sankeyplots.ipynb

{
 "cells": [
  {
   "cell_type": "code",
   "execution_count": 3,
   "metadata": {},
   "outputs": [],
   "source": [
    "run SPaircraft"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": 4,
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Beginning signomial solve.\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmp4yojzc\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.02            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.08    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6437              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.16              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.11            \n",
      "Factor     - nonzeros before factor : 2.65e+004         after factor           : 6.45e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.62e+006       \n",
      "Factor     - GP saved nzs           : 6.39e+004         GP saved flops         : 2.69e+006       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.322065908e+005 3.796372382e+002  1.0e+000 0.25  \n",
      "1   2.6e+003 3.2e+003 1.8e+005 -9.70e-001 -2.293566729e+005 2.122613972e+003  7.9e-001 0.27  \n",
      "2   1.4e+003 1.7e+003 1.0e+005 -9.60e-001 -2.193442646e+005 7.811000656e+003  4.3e-001 0.28  \n",
      "3   4.1e+002 5.0e+002 2.8e+004 -9.19e-001 -1.762200940e+005 2.856232242e+004  1.2e-001 0.30  \n",
      "4   3.1e+002 3.8e+002 2.2e+004 -7.04e-001 -1.730582965e+005 2.109673292e+004  9.4e-002 0.31  \n",
      "5   9.7e+001 1.2e+002 6.7e+003 -6.13e-001 -1.095703921e+005 2.448270815e+004  2.9e-002 0.33  \n",
      "6   6.1e+001 7.3e+001 4.2e+003 -7.68e-002 -8.356115177e+004 2.084464195e+004  1.8e-002 0.33  \n",
      "7   2.9e+001 3.5e+001 2.0e+003 1.77e-001  -4.887029510e+004 1.467731005e+004  8.8e-003 0.34  \n",
      "8   1.3e+001 1.6e+001 9.0e+002 5.26e-001  -2.348817343e+004 8.760611724e+003  3.9e-003 0.36  \n",
      "9   6.6e+000 8.0e+000 4.6e+002 7.88e-001  -1.201404033e+004 5.158529076e+003  2.0e-003 0.38  \n",
      "10  3.4e+000 4.2e+000 2.4e+002 9.05e-001  -6.000233422e+003 3.101475371e+003  1.0e-003 0.39  \n",
      "11  1.4e+000 1.6e+000 9.4e+001 9.61e-001  -2.292281068e+003 1.335209579e+003  4.1e-004 0.41  \n",
      "12  9.4e-001 1.1e+000 6.5e+001 9.88e-001  -1.518875856e+003 1.012607012e+003  2.8e-004 0.41  \n",
      "13  4.8e-001 5.8e-001 3.4e+001 9.91e-001  -6.838980707e+002 6.230272808e+002  1.5e-004 0.42  \n",
      "14  2.8e-001 3.6e-001 1.9e+001 9.93e-001  -3.063071307e+002 4.507347998e+002  8.5e-005 0.44  \n",
      "15  1.3e-001 4.2e-001 9.5e+000 9.76e-001  -5.098018800e+001 3.232739252e+002  4.2e-005 0.45  \n",
      "16  9.6e-002 3.0e-001 6.8e+000 9.95e-001  2.335677842e+001  2.903333505e+002  3.0e-005 0.47  \n",
      "17  3.1e-002 1.6e-001 2.2e+000 9.95e-001  1.468632822e+002  2.339936268e+002  9.9e-006 0.48  \n",
      "18  7.5e-003 1.7e-001 5.6e-001 9.99e-001  1.915366934e+002  2.136253414e+002  2.6e-006 0.50  \n",
      "19  2.2e-003 1.6e-001 1.7e-001 1.00e+000  2.022208725e+002  2.088498900e+002  7.8e-007 0.52  \n",
      "20  7.2e-004 1.8e-001 5.5e-002 1.00e+000  2.053451532e+002  2.075191272e+002  2.6e-007 0.52  \n",
      "21  5.1e-004 1.4e-001 3.9e-002 1.00e+000  2.057838904e+002  2.073241786e+002  1.8e-007 0.53  \n",
      "22  4.6e-004 1.2e-001 3.5e-002 1.00e+000  2.058965964e+002  2.072829503e+002  1.6e-007 0.55  \n",
      "23  2.0e-004 1.0e-001 1.6e-002 1.00e+000  2.064393073e+002  2.070505015e+002  7.2e-008 0.58  \n",
      "24  1.8e-004 9.4e-002 1.4e-002 1.00e+000  2.064830539e+002  2.070331228e+002  6.5e-008 0.59  \n",
      "25  1.6e-004 8.6e-002 1.3e-002 1.00e+000  2.065215457e+002  2.070165762e+002  5.8e-008 0.61  \n",
      "26  1.5e-004 7.8e-002 1.1e-002 1.00e+000  2.065562235e+002  2.070017288e+002  5.3e-008 0.63  \n",
      "27  1.3e-004 7.1e-002 1.0e-002 1.00e+000  2.065873770e+002  2.069883129e+002  4.7e-008 0.64  \n",
      "28  1.2e-004 6.5e-002 9.2e-003 1.00e+000  2.066153926e+002  2.069762193e+002  4.3e-008 0.67  \n",
      "29  1.1e-004 6.0e-002 8.3e-003 1.00e+000  2.066405897e+002  2.069653209e+002  3.8e-008 0.69  \n",
      "30  9.7e-005 5.5e-002 7.4e-003 1.00e+000  2.066632532e+002  2.069555008e+002  3.5e-008 0.70  \n",
      "31  8.8e-005 5.0e-002 6.7e-003 1.00e+000  2.066836387e+002  2.069466528e+002  3.1e-008 0.70  \n",
      "32  7.9e-005 4.6e-002 6.0e-003 1.00e+000  2.067019755e+002  2.069386811e+002  2.8e-008 0.72  \n",
      "33  7.1e-005 4.3e-002 5.4e-003 1.00e+000  2.067184701e+002  2.069314993e+002  2.5e-008 0.73  \n",
      "34  6.4e-005 3.9e-002 4.9e-003 1.00e+000  2.067333078e+002  2.069250294e+002  2.3e-008 0.75  \n",
      "35  5.7e-005 3.6e-002 4.4e-003 1.00e+000  2.067466557e+002  2.069192013e+002  2.0e-008 0.77  \n",
      "36  5.2e-005 3.4e-002 4.0e-003 1.00e+000  2.067586638e+002  2.069139517e+002  1.8e-008 0.78  \n",
      "37  4.7e-005 3.1e-002 3.6e-003 1.00e+000  2.067694669e+002  2.069092235e+002  1.7e-008 0.78  \n",
      "38  4.2e-005 2.9e-002 3.2e-003 1.00e+000  2.067791863e+002  2.069049652e+002  1.5e-008 0.80  \n",
      "39  3.8e-005 2.7e-002 2.9e-003 1.00e+000  2.067879310e+002  2.069011305e+002  1.3e-008 0.81  \n",
      "40  3.4e-005 2.5e-002 2.6e-003 1.00e+000  2.067957991e+002  2.068976773e+002  1.2e-008 0.83  \n",
      "41  3.1e-005 2.4e-002 2.3e-003 1.00e+000  2.068028785e+002  2.068945679e+002  1.1e-008 0.84  \n",
      "42  2.7e-005 2.2e-002 2.1e-003 1.00e+000  2.068092486e+002  2.068917682e+002  9.8e-009 0.84  \n",
      "43  2.5e-005 2.1e-002 1.9e-003 1.00e+000  2.068149804e+002  2.068892474e+002  8.8e-009 0.86  \n",
      "44  2.2e-005 2.0e-002 1.7e-003 1.00e+000  2.068201381e+002  2.068869779e+002  7.9e-009 0.88  \n",
      "45  2.0e-005 1.9e-002 1.5e-003 1.00e+000  2.068247792e+002  2.068849346e+002  7.1e-009 0.89  \n",
      "46  1.8e-005 1.8e-002 1.4e-003 1.00e+000  2.068289556e+002  2.068830951e+002  6.4e-009 0.91  \n",
      "47  1.6e-005 1.7e-002 1.2e-003 1.00e+000  2.068327136e+002  2.068814390e+002  5.8e-009 0.91  \n",
      "48  1.5e-005 1.6e-002 1.1e-003 1.00e+000  2.068360954e+002  2.068799481e+002  5.2e-009 0.92  \n",
      "49  1.3e-005 1.6e-002 1.0e-003 1.00e+000  2.068391386e+002  2.068786058e+002  4.7e-009 0.94  \n",
      "50  1.2e-005 1.5e-002 9.0e-004 1.00e+000  2.068418771e+002  2.068773975e+002  4.2e-009 0.95  \n",
      "51  1.1e-005 1.5e-002 8.1e-004 1.00e+000  2.068443414e+002  2.068763097e+002  3.8e-009 0.97  \n",
      "52  9.6e-006 1.4e-002 7.3e-004 1.00e+000  2.068465590e+002  2.068753304e+002  3.4e-009 0.98  \n",
      "53  8.6e-006 1.4e-002 6.6e-004 1.00e+000  2.068485546e+002  2.068744489e+002  3.1e-009 1.00  \n",
      "54  7.8e-006 1.3e-002 5.9e-004 1.00e+000  2.068503505e+002  2.068736552e+002  2.8e-009 1.01  \n",
      "55  7.0e-006 1.3e-002 5.3e-004 1.00e+000  2.068519666e+002  2.068729408e+002  2.5e-009 1.03  \n",
      "56  6.3e-006 1.3e-002 4.8e-004 1.00e+000  2.068534209e+002  2.068722977e+002  2.2e-009 1.05  \n",
      "57  5.7e-006 1.2e-002 4.3e-004 1.00e+000  2.068547296e+002  2.068717188e+002  2.0e-009 1.06  \n",
      "58  5.1e-006 1.2e-002 3.9e-004 1.00e+000  2.068559074e+002  2.068711977e+002  1.8e-009 1.06  \n",
      "59  4.6e-006 1.2e-002 3.5e-004 1.00e+000  2.068569673e+002  2.068707286e+002  1.6e-009 1.08  \n",
      "60  4.1e-006 1.2e-002 3.2e-004 1.00e+000  2.068579212e+002  2.068703063e+002  1.5e-009 1.09  \n",
      "61  3.7e-006 1.1e-002 2.8e-004 1.00e+000  2.068587796e+002  2.068699262e+002  1.3e-009 1.11  \n",
      "62  3.3e-006 1.1e-002 2.6e-004 1.00e+000  2.068595521e+002  2.068695840e+002  1.2e-009 1.13  \n",
      "63  3.0e-006 1.1e-002 2.3e-004 1.00e+000  2.068602472e+002  2.068692760e+002  1.1e-009 1.14  \n",
      "64  2.7e-006 1.1e-002 2.1e-004 1.00e+000  2.068608729e+002  2.068689988e+002  9.6e-010 1.14  \n",
      "65  2.4e-006 1.1e-002 1.9e-004 1.00e+000  2.068614359e+002  2.068687492e+002  8.7e-010 1.16  \n",
      "66  2.2e-006 1.1e-002 1.7e-004 1.00e+000  2.068619426e+002  2.068685246e+002  7.8e-010 1.17  \n",
      "67  2.0e-006 1.1e-002 1.5e-004 1.00e+000  2.068623986e+002  2.068683224e+002  7.0e-010 1.19  \n",
      "68  1.8e-006 1.1e-002 1.4e-004 1.00e+000  2.068628090e+002  2.068681404e+002  6.3e-010 1.20  \n",
      "69  1.6e-006 1.0e-002 1.2e-004 1.00e+000  2.068631783e+002  2.068679766e+002  5.7e-010 1.22  \n",
      "70  1.4e-006 1.0e-002 1.1e-004 1.00e+000  2.068635107e+002  2.068678291e+002  5.1e-010 1.23  \n",
      "71  1.3e-006 1.0e-002 9.9e-005 1.00e+000  2.068638098e+002  2.068676964e+002  4.6e-010 1.25  \n",
      "72  1.2e-006 1.0e-002 8.9e-005 1.00e+000  2.068640790e+002  2.068675769e+002  4.1e-010 1.25  \n",
      "73  1.0e-006 1.0e-002 8.0e-005 1.00e+000  2.068643212e+002  2.068674694e+002  3.7e-010 1.26  \n",
      "74  9.4e-007 1.0e-002 7.2e-005 1.00e+000  2.068645392e+002  2.068673726e+002  3.4e-010 1.28  \n",
      "75  8.5e-007 1.0e-002 6.5e-005 1.00e+000  2.068647355e+002  2.068672855e+002  3.0e-010 1.30  \n",
      "76  7.6e-007 1.0e-002 5.8e-005 1.00e+000  2.068649120e+002  2.068672071e+002  2.7e-010 1.31  \n",
      "77  6.9e-007 1.0e-002 5.3e-005 1.00e+000  2.068650710e+002  2.068671365e+002  2.4e-010 1.33  \n",
      "78  6.2e-007 1.0e-002 4.7e-005 1.00e+000  2.068652140e+002  2.068670730e+002  2.2e-010 1.34  \n",
      "79  5.6e-007 1.0e-002 4.3e-005 1.00e+000  2.068653427e+002  2.068670158e+002  2.0e-010 1.36  \n",
      "80  5.0e-007 1.0e-002 3.8e-005 1.00e+000  2.068654585e+002  2.068669643e+002  1.8e-010 1.36  \n",
      "81  4.5e-007 9.9e-003 3.5e-005 1.00e+000  2.068655628e+002  2.068669180e+002  1.6e-010 1.38  \n",
      "82  4.1e-007 9.9e-003 3.1e-005 1.00e+000  2.068656566e+002  2.068668763e+002  1.4e-010 1.39  \n",
      "83  3.7e-007 9.9e-003 2.8e-005 1.00e+000  2.068657410e+002  2.068668387e+002  1.3e-010 1.41  \n",
      "84  3.3e-007 9.9e-003 2.5e-005 1.00e+000  2.068658170e+002  2.068668050e+002  1.2e-010 1.42  \n",
      "85  3.0e-007 9.9e-003 2.3e-005 1.00e+000  2.068658854e+002  2.068667746e+002  1.1e-010 1.42  \n",
      "86  2.7e-007 9.8e-003 2.0e-005 1.00e+000  2.068659469e+002  2.068667472e+002  9.5e-011 1.44  \n",
      "87  2.4e-007 9.8e-003 1.8e-005 1.00e+000  2.068660023e+002  2.068667225e+002  8.5e-011 1.45  \n",
      "88  2.2e-007 9.8e-003 1.7e-005 1.00e+000  2.068660522e+002  2.068667004e+002  7.7e-011 1.47  \n",
      "89  1.9e-007 9.8e-003 1.5e-005 1.00e+000  2.068660970e+002  2.068666804e+002  6.9e-011 1.50  \n",
      "90  1.7e-007 9.8e-003 1.3e-005 1.00e+000  2.068661374e+002  2.068666625e+002  6.2e-011 1.50  \n",
      "91  1.6e-007 9.8e-003 1.2e-005 1.00e+000  2.068661738e+002  2.068666463e+002  5.6e-011 1.51  \n",
      "92  1.4e-007 9.8e-003 1.1e-005 1.00e+000  2.068662065e+002  2.068666317e+002  5.0e-011 1.53  \n",
      "93  1.3e-007 9.7e-003 9.7e-006 1.00e+000  2.068662359e+002  2.068666186e+002  4.5e-011 1.55  \n",
      "94  1.1e-007 9.7e-003 8.8e-006 1.00e+000  2.068662624e+002  2.068666069e+002  4.1e-011 1.58  \n",
      "95  1.0e-007 9.7e-003 7.9e-006 9.99e-001  2.068662862e+002  2.068665963e+002  3.7e-011 1.59  \n",
      "96  9.3e-008 9.7e-003 7.1e-006 1.00e+000  2.068663077e+002  2.068665867e+002  3.3e-011 1.61  \n",
      "97  8.4e-008 9.7e-003 6.4e-006 1.00e+000  2.068663270e+002  2.068665781e+002  3.0e-011 1.63  \n",
      "98  7.5e-008 9.7e-003 5.8e-006 9.99e-001  2.068663443e+002  2.068665704e+002  2.7e-011 1.64  \n",
      "99  6.8e-008 9.7e-003 5.2e-006 1.00e+000  2.068663600e+002  2.068665634e+002  2.4e-011 1.66  \n",
      "100 6.1e-008 9.7e-003 4.7e-006 9.98e-001  2.068663741e+002  2.068665572e+002  2.2e-011 1.67  \n",
      "101 5.5e-008 9.7e-003 4.2e-006 9.98e-001  2.068663867e+002  2.068665516e+002  1.9e-011 1.67  \n",
      "102 4.9e-008 9.7e-003 3.8e-006 9.98e-001  2.068663981e+002  2.068665465e+002  1.8e-011 1.69  \n",
      "103 4.4e-008 9.6e-003 3.4e-006 9.98e-001  2.068664084e+002  2.068665419e+002  1.6e-011 1.70  \n",
      "104 4.0e-008 8.7e-003 3.1e-006 1.00e+000  2.068664176e+002  2.068665378e+002  1.4e-011 1.72  \n",
      "105 3.6e-008 7.8e-003 2.8e-006 9.98e-001  2.068664259e+002  2.068665341e+002  1.3e-011 1.73  \n",
      "106 3.2e-008 7.0e-003 2.5e-006 1.00e+000  2.068664335e+002  2.068665307e+002  1.2e-011 1.75  \n",
      "107 2.9e-008 6.3e-003 2.2e-006 9.94e-001  2.068664402e+002  2.068665277e+002  1.0e-011 1.76  \n",
      "108 2.6e-008 5.7e-003 2.0e-006 1.00e+000  2.068664463e+002  2.068665250e+002  9.3e-012 1.76  \n",
      "109 2.4e-008 5.1e-003 1.8e-006 9.91e-001  2.068664517e+002  2.068665226e+002  8.4e-012 1.78  \n",
      "110 2.1e-008 4.6e-003 1.6e-006 1.00e+000  2.068664567e+002  2.068665204e+002  7.6e-012 1.80  \n",
      "111 1.9e-008 4.2e-003 1.5e-006 1.01e+000  2.068664613e+002  2.068665183e+002  6.8e-012 1.81  \n",
      "112 1.7e-008 3.7e-003 1.3e-006 9.98e-001  2.068664652e+002  2.068665166e+002  6.2e-012 1.83  \n",
      "113 1.5e-008 3.4e-003 1.2e-006 9.94e-001  2.068664688e+002  2.068665150e+002  5.5e-012 1.84  \n",
      "114 1.4e-008 3.0e-003 1.1e-006 9.85e-001  2.068664720e+002  2.068665136e+002  5.0e-012 1.86  \n",
      "115 1.3e-008 2.7e-003 9.6e-007 1.01e+000  2.068664749e+002  2.068665123e+002  4.5e-012 1.88  \n",
      "116 1.1e-008 2.5e-003 8.6e-007 1.00e+000  2.068664775e+002  2.068665111e+002  4.1e-012 1.88  \n",
      "117 1.0e-008 2.2e-003 7.8e-007 1.00e+000  2.068664798e+002  2.068665101e+002  3.7e-012 1.89  \n",
      "118 9.2e-009 2.0e-003 7.0e-007 1.02e+000  2.068664821e+002  2.068665090e+002  3.3e-012 1.91  \n",
      "119 8.2e-009 1.8e-003 6.3e-007 9.94e-001  2.068664839e+002  2.068665082e+002  3.0e-012 1.92  \n",
      "120 7.4e-009 1.6e-003 5.7e-007 9.79e-001  2.068664856e+002  2.068665075e+002  2.7e-012 1.94  \n",
      "121 6.7e-009 1.4e-003 5.1e-007 9.87e-001  2.068664871e+002  2.068665068e+002  2.4e-012 1.95  \n",
      "122 6.0e-009 1.3e-003 4.6e-007 1.00e+000  2.068664885e+002  2.068665062e+002  2.2e-012 1.95  \n",
      "123 5.4e-009 1.2e-003 4.1e-007 9.99e-001  2.068664897e+002  2.068665057e+002  2.0e-012 1.97  \n",
      "124 4.9e-009 1.1e-003 3.7e-007 9.97e-001  2.068664908e+002  2.068665052e+002  1.8e-012 1.98  \n",
      "125 4.7e-009 9.5e-004 3.3e-007 1.00e+000  2.068664918e+002  2.068665047e+002  1.6e-012 2.00  \n",
      "126 4.3e-009 8.6e-004 3.0e-007 9.96e-001  2.068664927e+002  2.068665043e+002  1.4e-012 2.00  \n",
      "127 3.8e-009 7.7e-004 2.7e-007 1.00e+000  2.068664935e+002  2.068665039e+002  1.3e-012 2.02  \n",
      "128 3.5e-009 6.9e-004 2.4e-007 9.95e-001  2.068664942e+002  2.068665036e+002  1.2e-012 2.03  \n",
      "129 6.5e-009 6.2e-004 2.2e-007 9.91e-001  2.068664949e+002  2.068665033e+002  1.0e-012 2.05  \n",
      "130 5.9e-009 5.6e-004 2.0e-007 9.97e-001  2.068664955e+002  2.068665031e+002  9.4e-013 2.06  \n",
      "Interior-point optimizer terminated. Time: 2.08. \n",
      "\n",
      "Optimizer terminated. Time: 2.13    \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 2.0686649547e+002   nrm: 4e+001   Viol.  con: 1e-007   var: 0e+000 \n",
      "  Dual.    obj: 2.0686650307e+002   nrm: 8e+002   Viol.  con: 0e+000   var: 3e-003 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 2.0686649547e+002   nrm: 4e+001   Viol.  con: 1e-007   var: 0e+000 \n",
      "  Dual.    obj: 2.0686650307e+002   nrm: 8e+002   Viol.  con: 0e+000   var: 3e-003 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 6.9338983793e+089\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmp4yojzc\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n",
      "Solving took 2.89 seconds.\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "result packing took 35% of solve time\n",
      "solution checking took 9.5% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmpzlln4e\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (504) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.00            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.09    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6427              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.14              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.11            \n",
      "Factor     - nonzeros before factor : 2.65e+004         after factor           : 6.44e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : 6.37e+004         GP saved flops         : 2.64e+006       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.318047951e+005 3.796372382e+002  1.0e+000 0.25  \n",
      "1   2.6e+003 3.2e+003 1.8e+005 -9.70e-001 -2.288617104e+005 2.176485921e+003  7.8e-001 0.27  \n",
      "2   1.4e+003 1.7e+003 9.7e+004 -9.60e-001 -2.184515682e+005 8.089159388e+003  4.2e-001 0.30  \n",
      "3   1.2e+003 1.5e+003 8.4e+004 -9.17e-001 -2.156206264e+005 9.295929151e+003  3.6e-001 0.31  \n",
      "4   4.1e+002 4.9e+002 2.8e+004 -9.02e-001 -1.782592665e+005 2.537859520e+004  1.2e-001 0.33  \n",
      "5   3.9e+002 4.7e+002 2.7e+004 -7.00e-001 -1.770285755e+005 2.484523704e+004  1.2e-001 0.34  \n",
      "6   3.3e+002 4.0e+002 2.3e+004 -6.82e-001 -1.720225097e+005 2.385750325e+004  9.8e-002 0.36  \n",
      "7   3.1e+002 3.8e+002 2.2e+004 -6.31e-001 -1.702257005e+005 2.376921617e+004  9.3e-002 0.38  \n",
      "8   2.6e+002 3.1e+002 1.8e+004 -6.12e-001 -1.627124887e+005 2.336090392e+004  7.7e-002 0.39  \n",
      "9   1.0e+002 1.2e+002 7.0e+003 -5.42e-001 -1.138503742e+005 2.287572512e+004  3.0e-002 0.41  \n",
      "10  5.2e+001 6.2e+001 3.5e+003 -1.07e-001 -7.515343433e+004 1.906351477e+004  1.5e-002 0.42  \n",
      "11  1.9e+001 2.3e+001 1.3e+003 2.61e-001  -3.308639607e+004 1.235197739e+004  5.7e-003 0.44  \n",
      "12  1.1e+001 1.4e+001 7.7e+002 6.81e-001  -2.014784243e+004 7.946956776e+003  3.3e-003 0.47  \n",
      "13  9.8e+000 1.2e+001 6.8e+002 8.21e-001  -1.763797499e+004 7.197404986e+003  2.9e-003 0.48  \n",
      "14  3.7e+000 4.4e+000 2.5e+002 8.46e-001  -6.631773988e+003 3.076307362e+003  1.1e-003 0.50  \n",
      "15  1.8e+000 2.2e+000 1.3e+002 9.58e-001  -3.276312631e+003 1.596315806e+003  5.5e-004 0.52  \n",
      "16  1.5e+000 1.9e+000 1.0e+002 9.72e-001  -2.639928361e+003 1.301280943e+003  4.4e-004 0.53  \n",
      "17  7.2e-001 9.1e-001 5.0e+001 9.81e-001  -1.288015136e+003 6.543229517e+002  2.2e-004 0.55  \n",
      "18  3.7e-001 4.8e-001 2.6e+001 9.94e-001  -6.338748023e+002 3.725235315e+002  1.1e-004 0.56  \n",
      "19  1.4e-001 2.4e-001 9.5e+000 9.97e-001  -2.084648521e+002 1.662923683e+002  4.2e-005 0.58  \n",
      "20  8.5e-002 1.9e-001 6.0e+000 9.98e-001  -1.144817696e+002 1.202168688e+002  2.6e-005 0.59  \n",
      "21  3.9e-002 1.3e-001 2.8e+000 1.00e+000  -2.954243070e+001 7.951247370e+001  1.2e-005 0.61  \n",
      "22  1.6e-002 1.1e-001 1.2e+000 1.00e+000  1.366384094e+001  5.891565894e+001  5.2e-006 0.63  \n",
      "23  6.8e-003 1.0e-001 5.0e-001 1.00e+000  3.121668773e+001  5.070136391e+001  2.2e-006 0.64  \n",
      "24  2.0e-003 1.4e-001 1.5e-001 1.00e+000  4.058182684e+001  4.646128493e+001  6.9e-007 0.67  \n",
      "25  6.6e-004 1.4e-001 4.9e-002 1.00e+000  4.331872875e+001  4.524625903e+001  2.3e-007 0.69  \n",
      "26  2.7e-004 1.2e-001 2.1e-002 1.00e+000  4.409930379e+001  4.490362768e+001  9.5e-008 0.70  \n",
      "27  1.3e-004 9.8e-002 9.7e-003 1.00e+000  4.438747075e+001  4.476485829e+001  4.5e-008 0.72  \n",
      "28  1.2e-004 8.9e-002 8.7e-003 1.00e+000  4.441462065e+001  4.475428438e+001  4.0e-008 0.73  \n",
      "29  1.0e-004 8.1e-002 7.8e-003 1.00e+000  4.443798246e+001  4.474366809e+001  3.6e-008 0.77  \n",
      "30  9.4e-005 7.4e-002 7.0e-003 1.00e+000  4.445895745e+001  4.473406452e+001  3.3e-008 0.78  \n",
      "31  8.4e-005 6.8e-002 6.3e-003 1.00e+000  4.447780978e+001  4.472539790e+001  2.9e-008 0.80  \n",
      "32  7.6e-005 6.2e-002 5.7e-003 1.00e+000  4.449476107e+001  4.471758367e+001  2.6e-008 0.81  \n",
      "33  6.8e-005 5.7e-002 5.1e-003 1.00e+000  4.451000518e+001  4.471054008e+001  2.4e-008 0.83  \n",
      "34  6.1e-005 5.2e-002 4.6e-003 1.00e+000  4.452371571e+001  4.470419272e+001  2.1e-008 0.84  \n",
      "35  5.5e-005 4.8e-002 4.2e-003 1.00e+000  4.453604823e+001  4.469847401e+001  1.9e-008 0.86  \n",
      "36  5.0e-005 4.4e-002 3.7e-003 1.00e+000  4.454714228e+001  4.469332265e+001  1.7e-008 0.86  \n",
      "37  4.5e-005 4.1e-002 3.4e-003 1.00e+000  4.455712297e+001  4.468868304e+001  1.6e-008 0.88  \n",
      "38  4.0e-005 3.8e-002 3.0e-003 1.00e+000  4.456610253e+001  4.468450479e+001  1.4e-008 0.89  \n",
      "39  3.6e-005 3.5e-002 2.7e-003 1.00e+000  4.457418170e+001  4.468074229e+001  1.3e-008 0.91  \n",
      "40  3.3e-005 3.2e-002 2.5e-003 1.00e+000  4.458145095e+001  4.467735434e+001  1.1e-008 0.92  \n",
      "41  2.9e-005 3.0e-002 2.2e-003 1.00e+000  4.458799161e+001  4.467430376e+001  1.0e-008 0.92  \n",
      "42  2.6e-005 2.8e-002 2.0e-003 1.00e+000  4.459387680e+001  4.467155703e+001  9.2e-009 0.94  \n",
      "43  2.4e-005 2.6e-002 1.8e-003 1.00e+000  4.459917226e+001  4.466908391e+001  8.3e-009 0.95  \n",
      "44  2.1e-005 2.5e-002 1.6e-003 1.00e+000  4.460393714e+001  4.466685719e+001  7.4e-009 0.97  \n",
      "45  1.9e-005 2.3e-002 1.5e-003 1.00e+000  4.460822463e+001  4.466485235e+001  6.7e-009 0.98  \n",
      "46  1.7e-005 2.2e-002 1.3e-003 1.00e+000  4.461208259e+001  4.466304728e+001  6.0e-009 1.00  \n",
      "47  1.6e-005 2.1e-002 1.2e-003 1.00e+000  4.461555407e+001  4.466142210e+001  5.4e-009 1.08  \n",
      "48  1.4e-005 1.9e-002 1.1e-003 1.00e+000  4.461867780e+001  4.465995890e+001  4.9e-009 1.09  \n",
      "49  1.3e-005 1.9e-002 9.5e-004 1.00e+000  4.462148864e+001  4.465864152e+001  4.4e-009 1.11  \n",
      "50  1.1e-005 1.8e-002 8.6e-004 1.00e+000  4.462401793e+001  4.465745545e+001  4.0e-009 1.14  \n",
      "51  1.0e-005 1.7e-002 7.7e-004 1.00e+000  4.462629388e+001  4.465638761e+001  3.6e-009 1.16  \n",
      "52  9.2e-006 1.6e-002 6.9e-004 1.00e+000  4.462834188e+001  4.465542620e+001  3.2e-009 1.17  \n",
      "53  8.3e-006 1.6e-002 6.2e-004 1.00e+000  4.463018477e+001  4.465456062e+001  2.9e-009 1.19  \n",
      "54  7.5e-006 1.5e-002 5.6e-004 1.00e+000  4.463184308e+001  4.465378134e+001  2.6e-009 1.20  \n",
      "55  6.7e-006 1.4e-002 5.1e-004 1.00e+000  4.463333531e+001  4.465307974e+001  2.3e-009 1.20  \n",
      "56  6.0e-006 1.4e-002 4.6e-004 1.00e+000  4.463467809e+001  4.465244807e+001  2.1e-009 1.22  \n",
      "57  5.4e-006 1.4e-002 4.1e-004 1.00e+000  4.463588639e+001  4.465187942e+001  1.9e-009 1.23  \n",
      "58  4.9e-006 1.3e-002 3.7e-004 1.00e+000  4.463697369e+001  4.465136744e+001  1.7e-009 1.25  \n",
      "59  4.4e-006 1.3e-002 3.3e-004 1.00e+000  4.463795210e+001  4.465090650e+001  1.5e-009 1.27  \n",
      "60  4.0e-006 1.3e-002 3.0e-004 1.00e+000  4.463883253e+001  4.465049150e+001  1.4e-009 1.28  \n",
      "61  3.6e-006 1.2e-002 2.7e-004 1.00e+000  4.463962478e+001  4.465011791e+001  1.2e-009 1.30  \n",
      "62  3.2e-006 1.2e-002 2.4e-004 1.00e+000  4.464033771e+001  4.464978152e+001  1.1e-009 1.30  \n",
      "63  2.9e-006 1.2e-002 2.2e-004 1.00e+000  4.464097924e+001  4.464947868e+001  1.0e-009 1.31  \n",
      "64  2.6e-006 1.2e-002 2.0e-004 1.00e+000  4.464155652e+001  4.464920605e+001  9.0e-010 1.33  \n",
      "65  2.3e-006 1.1e-002 1.8e-004 1.00e+000  4.464207600e+001  4.464896059e+001  8.1e-010 1.34  \n",
      "66  2.1e-006 1.1e-002 1.6e-004 1.00e+000  4.464254344e+001  4.464873963e+001  7.3e-010 1.36  \n",
      "67  1.9e-006 1.1e-002 1.4e-004 1.00e+000  4.464296409e+001  4.464854068e+001  6.6e-010 1.38  \n",
      "68  1.7e-006 1.1e-002 1.3e-004 1.00e+000  4.464334261e+001  4.464836158e+001  5.9e-010 1.38  \n",
      "69  1.5e-006 1.1e-002 1.2e-004 1.00e+000  4.464368321e+001  4.464820038e+001  5.3e-010 1.39  \n",
      "70  5.7e-007 4.0e-003 4.3e-005 1.00e+000  4.464561505e+001  4.464728256e+001  2.0e-010 1.41  \n",
      "71  5.1e-007 3.6e-003 3.8e-005 1.00e+000  4.464572904e+001  4.464722985e+001  1.8e-010 1.44  \n",
      "72  2.9e-007 2.1e-003 2.2e-005 9.98e-001  4.464616275e+001  4.464702290e+001  1.0e-010 1.45  \n",
      "73  2.6e-007 1.9e-003 2.0e-005 1.00e+000  4.464622118e+001  4.464699530e+001  9.2e-011 1.58  \n",
      "74  1.5e-007 1.1e-003 1.1e-005 9.96e-001  4.464644688e+001  4.464688727e+001  5.2e-011 1.59  \n",
      "75  1.3e-007 9.5e-004 1.0e-005 1.00e+000  4.464647678e+001  4.464687315e+001  4.7e-011 1.61  \n",
      "76  1.2e-007 8.6e-004 9.1e-006 1.00e+000  4.464650398e+001  4.464686014e+001  4.2e-011 1.64  \n",
      "77  6.9e-008 4.8e-004 5.2e-006 9.98e-001  4.464660892e+001  4.464681004e+001  2.4e-011 1.66  \n",
      "78  6.2e-008 4.3e-004 4.6e-006 9.93e-001  4.464662255e+001  4.464680357e+001  2.1e-011 1.67  \n",
      "79  5.6e-008 3.9e-004 4.2e-006 9.86e-001  4.464663474e+001  4.464679784e+001  1.9e-011 1.69  \n",
      "80  5.0e-008 3.5e-004 3.8e-006 9.83e-001  4.464664576e+001  4.464679252e+001  1.7e-011 1.72  \n",
      "81  4.5e-008 3.2e-004 3.4e-006 1.01e+000  4.464665593e+001  4.464678769e+001  1.6e-011 1.73  \n",
      "82  4.1e-008 2.9e-004 3.0e-006 9.58e-001  4.464666480e+001  4.464678347e+001  1.4e-011 1.75  \n",
      "83  3.8e-008 2.6e-004 2.7e-006 1.01e+000  4.464667299e+001  4.464677964e+001  1.3e-011 1.77  \n",
      "84  3.5e-008 2.3e-004 2.5e-006 1.02e+000  4.464668069e+001  4.464677595e+001  1.2e-011 1.78  \n",
      "85  3.1e-008 2.1e-004 2.2e-006 9.91e-001  4.464668714e+001  4.464677273e+001  1.0e-011 1.80  \n",
      "86  7.6e-003 2.1e-004 2.2e-006 -2.20e-001 4.464668714e+001  4.464677273e+001  1.0e-011 1.80  \n",
      "87  6.8e-003 1.9e-004 2.0e-006 1.02e+000  4.464669250e+001  4.464677314e+001  9.5e-012 1.81  \n",
      "88  6.1e-003 6.0e-004 1.8e-006 1.03e+000  4.464669826e+001  4.464677139e+001  8.7e-012 1.83  \n",
      "89  5.5e-003 1.6e-003 1.6e-006 1.01e+000  4.464670313e+001  4.464676854e+001  7.9e-012 1.84  \n",
      "90  5.0e-003 2.3e-003 1.5e-006 9.81e-001  4.464670731e+001  4.464676615e+001  7.1e-012 1.86  \n",
      "91  4.5e-003 3.1e-003 1.3e-006 9.91e-001  4.464671106e+001  4.464676401e+001  6.4e-012 1.88  \n",
      "92  4.0e-003 2.7e-003 1.2e-006 1.02e+000  4.464671475e+001  4.464676175e+001  5.8e-012 1.91  \n",
      "93  3.6e-003 2.5e-003 1.1e-006 1.05e+000  4.464671846e+001  4.464675963e+001  5.3e-012 1.92  \n",
      "94  3.3e-003 2.2e-003 9.6e-007 9.48e-001  4.464672114e+001  4.464675786e+001  4.8e-012 1.94  \n",
      "95  2.9e-003 2.0e-003 8.6e-007 1.02e+000  4.464672363e+001  4.464675670e+001  4.4e-012 1.95  \n",
      "96  2.6e-003 1.8e-003 7.7e-007 1.08e+000  4.464672654e+001  4.464675510e+001  4.1e-012 1.97  \n",
      "97  2.4e-003 1.6e-003 7.0e-007 1.00e+000  4.464672838e+001  4.464675407e+001  3.7e-012 2.00  \n",
      "98  2.1e-003 1.5e-003 6.3e-007 1.00e+000  4.464673004e+001  4.464675314e+001  3.3e-012 2.02  \n",
      "99  1.9e-003 1.3e-003 5.6e-007 1.01e+000  4.464673157e+001  4.464675226e+001  3.0e-012 2.03  \n",
      "100 1.7e-003 1.2e-003 5.1e-007 1.01e+000  4.464673297e+001  4.464675148e+001  2.7e-012 2.05  \n",
      "101 1.6e-003 1.1e-003 4.6e-007 1.01e+000  4.464673420e+001  4.464675077e+001  2.5e-012 2.06  \n",
      "102 1.4e-003 9.6e-004 4.1e-007 1.01e+000  4.464673531e+001  4.464675014e+001  2.2e-012 2.08  \n",
      "103 1.3e-003 8.6e-004 3.7e-007 1.00e+000  4.464673628e+001  4.464674959e+001  2.0e-012 2.09  \n",
      "104 1.1e-003 7.8e-004 3.3e-007 9.84e-001  4.464673713e+001  4.464674914e+001  1.8e-012 2.11  \n",
      "105 1.0e-003 7.0e-004 3.0e-007 1.00e+000  4.464673790e+001  4.464674870e+001  1.6e-012 2.13  \n",
      "106 9.2e-004 6.3e-004 2.7e-007 9.98e-001  4.464673859e+001  4.464674831e+001  1.5e-012 2.14  \n",
      "107 8.3e-004 5.7e-004 2.4e-007 9.91e-001  4.464673922e+001  4.464674795e+001  1.3e-012 2.14  \n",
      "108 7.5e-004 5.1e-004 2.2e-007 9.77e-001  4.464673978e+001  4.464674764e+001  1.2e-012 2.16  \n",
      "109 6.7e-004 4.6e-004 2.0e-007 9.68e-001  4.464674028e+001  4.464674735e+001  1.1e-012 2.17  \n",
      "110 6.1e-004 4.1e-004 1.8e-007 9.47e-001  4.464674073e+001  4.464674710e+001  9.6e-013 2.19  \n",
      "Interior-point optimizer terminated. Time: 2.19. \n",
      "\n",
      "Optimizer terminated. Time: 2.25    \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 4.4646740732e+001   nrm: 4e+001   Viol.  con: 1e-002   var: 0e+000 \n",
      "  Dual.    obj: 4.4646747103e+001   nrm: 7e+002   Viol.  con: 0e+000   var: 2e-003 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 4.4646740732e+001   nrm: 4e+001   Viol.  con: 1e-002   var: 0e+000 \n",
      "  Dual.    obj: 4.4646747103e+001   nrm: 7e+002   Viol.  con: 0e+000   var: 2e-003 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 2.4537659462e+019\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmpzlln4e\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n",
      "Solving took 2.99 seconds.\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "result packing took 33% of solve time\n",
      "Solution check warning: sum of nu^T * A did not vanish\n",
      "solution checking took 5.2% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmpenqwyp\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.00            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.11    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6439              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.14              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.11            \n",
      "Factor     - nonzeros before factor : 2.66e+004         after factor           : 6.44e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : 6.38e+004         GP saved flops         : 2.64e+006       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.333557026e+005 3.796372382e+002  1.0e+000 0.25  \n",
      "1   2.6e+003 3.2e+003 1.8e+005 -9.70e-001 -2.303910902e+005 2.188977231e+003  7.8e-001 0.27  \n",
      "2   1.6e+003 1.9e+003 1.1e+005 -9.60e-001 -2.221687115e+005 6.850416576e+003  4.6e-001 0.30  \n",
      "3   1.3e+003 1.6e+003 9.0e+004 -9.26e-001 -2.188201041e+005 8.407648007e+003  3.9e-001 0.31  \n",
      "4   4.0e+002 4.9e+002 2.8e+004 -9.09e-001 -1.791386233e+005 2.600650015e+004  1.2e-001 0.31  \n",
      "5   3.8e+002 4.7e+002 2.7e+004 -7.01e-001 -1.778672734e+005 2.529381303e+004  1.1e-001 0.33  \n",
      "6   3.2e+002 3.9e+002 2.2e+004 -6.81e-001 -1.720958601e+005 2.446170604e+004  9.6e-002 0.34  \n",
      "7   3.1e+002 3.7e+002 2.1e+004 -6.26e-001 -1.706655283e+005 2.427113647e+004  9.2e-002 0.36  \n",
      "8   2.5e+002 3.1e+002 1.8e+004 -6.09e-001 -1.627621516e+005 2.381838495e+004  7.5e-002 0.38  \n",
      "9   1.4e+002 1.7e+002 9.4e+003 -5.37e-001 -1.315269707e+005 2.328682468e+004  4.1e-002 0.39  \n",
      "10  1.3e+002 1.6e+002 8.9e+003 -2.58e-001 -1.272484774e+005 2.436317556e+004  3.8e-002 0.41  \n",
      "11  4.7e+001 5.8e+001 3.3e+003 -2.28e-001 -7.261663986e+004 1.818702457e+004  1.4e-002 0.41  \n",
      "12  2.4e+001 2.9e+001 1.6e+003 2.96e-001  -4.162140401e+004 1.301420779e+004  7.1e-003 0.42  \n",
      "13  1.1e+001 1.3e+001 7.6e+002 6.00e-001  -2.064909242e+004 7.387347384e+003  3.3e-003 0.44  \n",
      "14  6.1e+000 7.4e+000 4.3e+002 8.24e-001  -1.137073167e+004 4.810431205e+003  1.8e-003 0.45  \n",
      "15  2.1e+000 2.6e+000 1.5e+002 9.16e-001  -3.951709194e+003 1.752304071e+003  6.3e-004 0.45  \n",
      "16  1.2e+000 1.4e+000 8.3e+001 9.86e-001  -2.196679744e+003 1.031714389e+003  3.6e-004 0.47  \n",
      "17  7.1e-001 8.7e-001 5.0e+001 9.91e-001  -1.317121652e+003 6.383411920e+002  2.2e-004 0.48  \n",
      "18  6.7e-001 1.4e+000 4.7e+001 9.64e-001  -1.255602779e+003 5.926510644e+002  2.0e-004 0.50  \n",
      "19  4.2e-001 8.9e-001 2.9e+001 9.78e-001  -7.892015422e+002 3.690858678e+002  1.3e-004 0.52  \n",
      "20  1.9e-001 4.3e-001 1.3e+001 9.97e-001  -3.505748327e+002 1.848359229e+002  5.9e-005 0.53  \n",
      "21  9.3e-002 2.2e-001 6.6e+000 9.98e-001  -1.593009874e+002 1.036793561e+002  2.9e-005 0.55  \n",
      "22  4.4e-002 1.6e-001 3.2e+000 1.00e+000  -6.558891176e+001 5.914579807e+001  1.4e-005 0.56  \n",
      "23  1.5e-002 1.3e-001 1.1e+000 1.00e+000  -8.344622287e+000 3.501606774e+001  4.9e-006 0.58  \n",
      "24  7.7e-003 1.6e-001 5.7e-001 1.00e+000  6.303296247e+000  2.885856623e+001  2.6e-006 0.59  \n",
      "25  4.5e-003 1.8e-001 3.4e-001 9.82e-001  1.283811649e+001  2.585876750e+001  1.5e-006 0.61  \n",
      "26  1.8e-003 1.2e-001 1.4e-001 8.32e-001  1.836331766e+001  2.380703342e+001  6.3e-007 0.64  \n",
      "27  5.0e-004 1.2e-001 4.1e-002 9.36e-001  2.113877527e+001  2.279484725e+001  1.9e-007 0.66  \n",
      "28  2.0e-004 1.2e-001 1.7e-002 1.02e+000  2.183049704e+001  2.250050015e+001  7.7e-008 0.67  \n",
      "29  8.4e-005 1.1e-001 7.1e-003 1.01e+000  2.210704617e+001  2.238687907e+001  3.2e-008 0.69  \n",
      "30  3.7e-005 1.0e-001 3.2e-003 9.98e-001  2.221535092e+001  2.233962044e+001  1.4e-008 0.70  \n",
      "31  1.9e-005 8.6e-002 1.6e-003 1.00e+000  2.225703408e+001  2.232153011e+001  7.5e-009 0.72  \n",
      "32  1.7e-005 7.8e-002 1.5e-003 1.00e+000  2.226159637e+001  2.231964483e+001  6.7e-009 0.73  \n",
      "33  1.6e-005 7.1e-002 1.3e-003 1.00e+000  2.226562118e+001  2.231786373e+001  6.1e-009 0.73  \n",
      "34  1.4e-005 6.5e-002 1.2e-003 1.00e+000  2.226924481e+001  2.231626207e+001  5.5e-009 0.75  \n",
      "35  1.3e-005 6.0e-002 1.1e-003 1.00e+000  2.227250309e+001  2.231481769e+001  4.9e-009 0.77  \n",
      "36  1.1e-005 5.5e-002 9.7e-004 1.00e+000  2.227543333e+001  2.231351568e+001  4.4e-009 0.78  \n",
      "37  1.0e-005 5.0e-002 8.7e-004 1.00e+000  2.227806853e+001  2.231234196e+001  4.0e-009 0.80  \n",
      "38  9.3e-006 4.6e-002 7.8e-004 1.00e+000  2.228043852e+001  2.231128405e+001  3.6e-009 0.80  \n",
      "39  8.4e-006 4.3e-002 7.0e-004 1.00e+000  2.228257016e+001  2.231033065e+001  3.2e-009 0.81  \n",
      "40  7.5e-006 3.9e-002 6.3e-004 1.00e+000  2.228448756e+001  2.230947161e+001  2.9e-009 0.83  \n",
      "41  6.8e-006 3.6e-002 5.7e-004 1.00e+000  2.228621239e+001  2.230869773e+001  2.6e-009 0.84  \n",
      "42  6.1e-006 3.4e-002 5.1e-004 1.00e+000  2.228776409e+001  2.230800062e+001  2.4e-009 0.86  \n",
      "43  5.5e-006 3.1e-002 4.6e-004 1.00e+000  2.228916010e+001  2.230737276e+001  2.1e-009 0.86  \n",
      "44  4.9e-006 2.9e-002 4.2e-004 1.00e+000  2.229041609e+001  2.230680731e+001  1.9e-009 0.88  \n",
      "45  4.4e-006 2.7e-002 3.7e-004 1.00e+000  2.229154614e+001  2.230629809e+001  1.7e-009 0.89  \n",
      "46  4.0e-006 2.6e-002 3.4e-004 1.00e+000  2.229256290e+001  2.230583954e+001  1.5e-009 0.91  \n",
      "47  3.6e-006 2.4e-002 3.0e-004 1.00e+000  2.229347774e+001  2.230542662e+001  1.4e-009 0.92  \n",
      "48  3.2e-006 2.3e-002 2.7e-004 1.00e+000  2.229430090e+001  2.230505480e+001  1.2e-009 0.94  \n",
      "49  2.9e-006 2.1e-002 2.5e-004 1.00e+000  2.229504157e+001  2.230472002e+001  1.1e-009 0.94  \n",
      "50  2.6e-006 2.0e-002 2.2e-004 1.00e+000  2.229570803e+001  2.230441860e+001  1.0e-009 0.95  \n",
      "51  2.4e-006 1.9e-002 2.0e-004 1.00e+000  2.229630772e+001  2.230414720e+001  9.1e-010 0.97  \n",
      "52  2.1e-006 1.8e-002 1.8e-004 1.00e+000  2.229684732e+001  2.230390288e+001  8.2e-010 0.98  \n",
      "53  7.9e-007 6.8e-003 6.7e-005 1.00e+000  2.229989031e+001  2.230251960e+001  3.1e-010 1.00  \n",
      "54  7.1e-007 6.8e-003 6.0e-005 1.00e+000  2.230007250e+001  2.230243925e+001  2.7e-010 1.02  \n",
      "55  1.7e-007 1.6e-003 1.4e-005 1.00e+000  2.230131749e+001  2.230186967e+001  6.4e-011 1.03  \n",
      "56  1.5e-007 1.4e-003 1.3e-005 9.94e-001  2.230135577e+001  2.230185243e+001  5.8e-011 1.03  \n",
      "57  2.6e-008 2.0e-004 1.8e-006 1.01e+000  2.230164780e+001  2.230171748e+001  8.0e-012 1.05  \n",
      "58  5.9e-008 3.0e-006 2.8e-008 8.55e-001  2.230169535e+001  2.230169644e+001  2.0e-013 1.06  \n",
      "Interior-point optimizer terminated. Time: 1.08. \n",
      "\n",
      "Optimizer terminated. Time: 1.17    \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 2.2301695354e+001   nrm: 3e+001   Viol.  con: 1e-006   var: 0e+000 \n",
      "  Dual.    obj: 2.2301696443e+001   nrm: 8e+002   Viol.  con: 0e+000   var: 2e-005 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 2.2301695354e+001   nrm: 3e+001   Viol.  con: 1e-006   var: 0e+000 \n",
      "  Dual.    obj: 2.2301696443e+001   nrm: 8e+002   Viol.  con: 0e+000   var: 2e-005 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 4.8473371678e+009\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmpenqwyp\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n",
      "Solving took 1.95 seconds.\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "result packing took 44% of solve time\n",
      "solution checking took 12% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmpbyrgm3\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (269) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (270) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.00            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.09    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6439              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.08              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.05            \n",
      "Factor     - nonzeros before factor : 2.66e+004         after factor           : 6.55e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : -1924             GP saved flops         : 6.58e+004       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.328051568e+005 3.796372382e+002  1.0e+000 0.17  \n",
      "1   2.6e+003 3.2e+003 1.8e+005 -9.70e-001 -2.299272785e+005 2.139384236e+003  7.8e-001 0.19  \n",
      "2   1.5e+003 1.8e+003 1.0e+005 -9.60e-001 -2.202381456e+005 7.641305737e+003  4.3e-001 0.20  \n",
      "3   4.1e+002 4.9e+002 2.8e+004 -9.21e-001 -1.764833909e+005 2.880046023e+004  1.2e-001 0.22  \n",
      "4   3.1e+002 3.8e+002 2.1e+004 -7.04e-001 -1.733787680e+005 2.107867175e+004  9.3e-002 0.23  \n",
      "5   1.8e+002 2.1e+002 1.2e+004 -6.12e-001 -1.455781509e+005 2.298472992e+004  5.2e-002 0.25  \n",
      "6   6.9e+001 8.4e+001 4.8e+003 -3.82e-001 -9.311036583e+004 2.010850898e+004  2.1e-002 0.27  \n",
      "7   3.9e+001 4.7e+001 2.7e+003 1.04e-001  -6.233384940e+004 1.652665159e+004  1.2e-002 0.28  \n",
      "8   2.1e+001 2.6e+001 1.5e+003 3.97e-001  -3.757418304e+004 1.155544444e+004  6.3e-003 0.28  \n",
      "9   9.4e+000 1.1e+001 6.5e+002 6.45e-001  -1.764422788e+004 6.467946314e+003  2.8e-003 0.30  \n",
      "10  5.3e+000 6.4e+000 3.7e+002 8.54e-001  -9.795218063e+003 4.158827998e+003  1.6e-003 0.31  \n",
      "11  1.6e+000 2.0e+000 1.1e+002 9.28e-001  -3.040190363e+003 1.301103607e+003  4.9e-004 0.33  \n",
      "12  1.1e+000 1.3e+000 7.5e+001 9.90e-001  -1.945385003e+003 9.752835957e+002  3.3e-004 0.34  \n",
      "13  7.4e-001 9.0e-001 5.2e+001 9.89e-001  -1.348457247e+003 6.721030646e+002  2.3e-004 0.36  \n",
      "14  6.2e-001 9.0e-001 4.3e+001 9.62e-001  -1.160757623e+003 5.561378524e+002  1.9e-004 0.38  \n",
      "15  3.9e-001 5.7e-001 2.8e+001 9.83e-001  -7.311776684e+002 3.532213349e+002  1.2e-004 0.39  \n",
      "16  1.8e-001 2.7e-001 1.2e+001 9.89e-001  -3.325719608e+002 1.573967162e+002  5.4e-005 0.41  \n",
      "17  1.2e-001 1.9e-001 8.5e+000 1.01e+000  -2.256065628e+002 1.111165526e+002  3.7e-005 0.42  \n",
      "18  4.9e-002 1.3e-001 3.5e+000 1.00e+000  -8.887031747e+001 5.003485942e+001  1.6e-005 0.44  \n",
      "19  4.5e-002 1.5e-001 3.3e+000 1.01e+000  -7.587160605e+001 5.140665159e+001  1.4e-005 0.47  \n",
      "20  3.6e-002 1.2e-001 2.6e+000 1.00e+000  -5.946780035e+001 4.321477203e+001  1.2e-005 0.48  \n",
      "21  9.6e-003 1.7e-001 7.2e-001 9.99e-001  -8.406573302e+000 1.994995187e+001  3.3e-006 0.50  \n",
      "22  4.4e-003 1.2e-001 3.4e-001 1.01e+000  2.251869575e+000  1.543086471e+001  1.5e-006 0.52  \n",
      "23  9.0e-004 1.9e-001 7.3e-002 1.00e+000  9.698301792e+000  1.252210290e+001  3.4e-007 0.53  \n",
      "24  3.8e-004 1.8e-001 3.1e-002 1.00e+000  1.086935461e+001  1.207407666e+001  1.5e-007 0.53  \n",
      "25  3.1e-004 1.8e-001 2.5e-002 9.81e-001  1.102849635e+001  1.198779208e+001  1.2e-007 0.55  \n",
      "26  1.9e-004 1.4e-001 1.6e-002 7.72e-001  1.128783932e+001  1.186925051e+001  7.4e-008 0.56  \n",
      "27  5.0e-005 1.1e-001 4.6e-003 7.76e-001  1.159567759e+001  1.177862199e+001  2.2e-008 0.58  \n",
      "28  4.6e-005 1.1e-001 4.3e-003 1.04e+000  1.161087225e+001  1.177573167e+001  2.0e-008 0.59  \n",
      "29  4.3e-005 1.0e-001 4.0e-003 1.01e+000  1.161906821e+001  1.177231100e+001  1.9e-008 0.63  \n",
      "30  3.9e-005 9.7e-002 3.6e-003 1.00e+000  1.162957302e+001  1.176731747e+001  1.7e-008 0.64  \n",
      "31  3.5e-005 8.9e-002 3.2e-003 1.00e+000  1.163925264e+001  1.176319112e+001  1.5e-008 0.66  \n",
      "32  3.2e-005 8.1e-002 2.9e-003 1.00e+000  1.164793313e+001  1.175948285e+001  1.4e-008 0.67  \n",
      "33  2.8e-005 7.3e-002 2.6e-003 1.00e+000  1.165574320e+001  1.175614162e+001  1.2e-008 0.69  \n",
      "34  2.6e-005 6.7e-002 2.4e-003 1.00e+000  1.166276854e+001  1.175313046e+001  1.1e-008 0.70  \n",
      "35  1.1e-005 2.9e-002 1.0e-003 1.00e+000  1.169852546e+001  1.173777523e+001  4.8e-009 0.73  \n",
      "36  1.0e-005 2.7e-002 9.2e-004 1.00e+000  1.170124369e+001  1.173657018e+001  4.3e-009 0.75  \n",
      "37  9.0e-006 2.5e-002 8.3e-004 1.00e+000  1.170372951e+001  1.173552466e+001  3.9e-009 0.77  \n",
      "38  3.6e-006 1.0e-002 3.4e-004 1.00e+000  1.171689130e+001  1.172981358e+001  1.6e-009 0.78  \n",
      "39  3.3e-006 9.8e-003 3.0e-004 1.00e+000  1.171781468e+001  1.172944547e+001  1.4e-009 0.80  \n",
      "40  1.3e-006 3.7e-003 1.2e-004 1.00e+000  1.172281291e+001  1.172726214e+001  5.5e-010 0.81  \n",
      "41  1.1e-006 3.4e-003 1.0e-004 1.00e+000  1.172312649e+001  1.172713092e+001  4.9e-010 0.83  \n",
      "42  4.3e-007 1.3e-003 4.0e-005 1.00e+000  1.172485067e+001  1.172637560e+001  1.9e-010 0.83  \n",
      "43  3.9e-007 1.1e-003 3.6e-005 9.99e-001  1.172495704e+001  1.172632988e+001  1.7e-010 0.84  \n",
      "44  9.1e-008 2.7e-004 8.4e-006 1.00e+000  1.172568518e+001  1.172600972e+001  4.0e-011 0.86  \n",
      "45  8.3e-008 2.4e-004 7.6e-006 1.00e+000  1.172570826e+001  1.172599929e+001  3.6e-011 0.88  \n",
      "46  3.2e-008 5.1e-005 1.6e-006 1.01e+000  1.172586857e+001  1.172592954e+001  7.6e-012 0.89  \n",
      "47  2.3e-008 3.2e-006 1.0e-007 9.96e-001  1.172590787e+001  1.172591169e+001  4.7e-013 0.91  \n",
      "Interior-point optimizer terminated. Time: 0.92. \n",
      "\n",
      "Optimizer terminated. Time: 0.97    \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.1725907867e+001   nrm: 2e+001   Viol.  con: 7e-007   var: 0e+000 \n",
      "  Dual.    obj: 1.1725911687e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 2e-005 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.1725907867e+001   nrm: 2e+001   Viol.  con: 7e-007   var: 0e+000 \n",
      "  Dual.    obj: 1.1725911687e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 2e-005 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 1.2373628763e+005\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmpbyrgm3\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n",
      "Solving took 1.74 seconds.\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "result packing took 82% of solve time\n",
      "solution checking took 29% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmpazzfbw\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (269) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (270) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (505) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.00            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.09    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6439              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.11              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.06            \n",
      "Factor     - nonzeros before factor : 2.66e+004         after factor           : 6.55e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : -1924             GP saved flops         : 6.58e+004       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.325689449e+005 3.796372382e+002  1.0e+000 0.20  \n",
      "1   2.7e+003 3.2e+003 1.8e+005 -9.70e-001 -2.297406199e+005 2.106381772e+003  7.9e-001 0.22  \n",
      "2   1.4e+003 1.7e+003 9.9e+004 -9.60e-001 -2.195382644e+005 7.946424781e+003  4.3e-001 0.23  \n",
      "3   4.1e+002 4.9e+002 2.8e+004 -9.19e-001 -1.760459014e+005 2.886849292e+004  1.2e-001 0.23  \n",
      "4   3.1e+002 3.7e+002 2.1e+004 -7.02e-001 -1.724723509e+005 2.156929350e+004  9.2e-002 0.25  \n",
      "5   1.0e+002 1.3e+002 7.2e+003 -6.10e-001 -1.142172626e+005 2.453665754e+004  3.1e-002 0.27  \n",
      "6   5.6e+001 6.8e+001 3.9e+003 -1.17e-001 -7.971324673e+004 2.017984827e+004  1.7e-002 0.28  \n",
      "7   3.3e+001 4.0e+001 2.3e+003 2.19e-001  -5.432140844e+004 1.579039417e+004  1.0e-002 0.30  \n",
      "8   1.7e+001 2.0e+001 1.2e+003 4.72e-001  -3.037169067e+004 1.012533418e+004  5.0e-003 0.33  \n",
      "9   5.8e+000 7.1e+000 4.0e+002 7.19e-001  -1.081610436e+004 4.484541219e+003  1.7e-003 0.34  \n",
      "10  3.3e+000 4.0e+000 2.3e+002 9.23e-001  -6.089432289e+003 2.733156155e+003  1.0e-003 0.34  \n",
      "11  1.4e+000 1.7e+000 9.9e+001 9.66e-001  -2.663992538e+003 1.152397698e+003  4.3e-004 0.36  \n",
      "12  8.2e-001 9.9e-001 5.7e+001 9.90e-001  -1.488174073e+003 7.215981208e+002  2.5e-004 0.38  \n",
      "13  7.8e-001 9.5e-001 5.4e+001 9.76e-001  -1.438067010e+003 6.860798159e+002  2.4e-004 0.39  \n",
      "14  5.7e-001 7.0e-001 4.0e+001 9.71e-001  -1.086643296e+003 4.964452658e+002  1.8e-004 0.41  \n",
      "15  3.1e-001 3.8e-001 2.2e+001 9.87e-001  -5.796876871e+002 2.745810725e+002  9.5e-005 0.41  \n",
      "16  1.2e-001 1.8e-001 8.8e+000 9.92e-001  -2.369005202e+002 1.091627042e+002  3.9e-005 0.42  \n",
      "17  9.9e-002 1.4e-001 7.0e+000 1.01e+000  -1.856521506e+002 8.935779717e+001  3.1e-005 0.44  \n",
      "18  5.1e-002 1.1e-001 3.6e+000 1.01e+000  -9.311368646e+001 4.910656808e+001  1.6e-005 0.45  \n",
      "19  5.0e-002 1.1e-001 3.5e+000 1.01e+000  -9.007359200e+001 4.885199196e+001  1.6e-005 0.47  \n",
      "20  3.0e-002 9.0e-002 2.2e+000 1.01e+000  -4.999151600e+001 3.516465312e+001  9.7e-006 0.48  \n",
      "21  1.9e-002 1.6e-001 1.4e+000 1.01e+000  -2.826553040e+001 2.537208734e+001  6.1e-006 0.50  \n",
      "22  7.6e-003 2.0e-001 5.6e-001 1.00e+000  -5.692312453e+000 1.593362762e+001  2.5e-006 0.50  \n",
      "23  6.5e-003 1.6e-001 4.8e-001 1.01e+000  -2.562458182e+000 1.598832787e+001  2.2e-006 0.52  \n",
      "24  1.3e-003 1.6e-001 1.0e-001 1.00e+000  8.328206774e+000  1.220838956e+001  4.5e-007 0.53  \n",
      "25  5.8e-004 1.2e-001 4.6e-002 1.02e+000  9.778519842e+000  1.151431712e+001  2.0e-007 0.55  \n",
      "26  2.2e-004 1.2e-001 1.8e-002 1.01e+000  1.053127509e+001  1.120315971e+001  8.0e-008 0.56  \n",
      "27  1.1e-004 1.1e-001 8.9e-003 1.01e+000  1.076906326e+001  1.110361794e+001  4.0e-008 0.56  \n",
      "28  9.9e-005 9.6e-002 8.0e-003 1.01e+000  1.079499301e+001  1.109628115e+001  3.6e-008 0.58  \n",
      "29  8.9e-005 8.7e-002 7.2e-003 1.01e+000  1.081504898e+001  1.108611959e+001  3.3e-008 0.59  \n",
      "30  8.0e-005 8.0e-002 6.5e-003 1.01e+000  1.083339408e+001  1.107729987e+001  2.9e-008 0.61  \n",
      "31  7.2e-005 7.3e-002 5.8e-003 1.01e+000  1.084982462e+001  1.106928836e+001  2.6e-008 0.63  \n",
      "32  6.5e-005 6.7e-002 5.2e-003 1.01e+000  1.086459143e+001  1.106206682e+001  2.4e-008 0.64  \n",
      "33  5.9e-005 6.1e-002 4.7e-003 1.00e+000  1.087785464e+001  1.105554788e+001  2.1e-008 0.64  \n",
      "34  5.3e-005 5.6e-002 4.2e-003 1.00e+000  1.088977017e+001  1.104966569e+001  1.9e-008 0.67  \n",
      "35  4.8e-005 5.1e-002 3.8e-003 1.00e+000  1.090047557e+001  1.104435826e+001  1.7e-008 0.69  \n",
      "36  4.3e-005 4.7e-002 3.4e-003 1.00e+000  1.091009463e+001  1.103956999e+001  1.6e-008 0.69  \n",
      "37  3.8e-005 4.4e-002 3.1e-003 1.00e+000  1.091873827e+001  1.103525057e+001  1.4e-008 0.70  \n",
      "38  3.5e-005 4.0e-002 2.8e-003 1.00e+000  1.092650603e+001  1.103135441e+001  1.3e-008 0.72  \n",
      "39  3.1e-005 3.7e-002 2.5e-003 1.00e+000  1.093348717e+001  1.102784040e+001  1.1e-008 0.73  \n",
      "40  2.8e-005 3.5e-002 2.3e-003 1.00e+000  1.093976184e+001  1.102467137e+001  1.0e-008 0.75  \n",
      "41  2.5e-005 3.2e-002 2.0e-003 1.00e+000  1.094540191e+001  1.102181365e+001  9.2e-009 0.77  \n",
      "42  2.3e-005 3.0e-002 1.8e-003 1.00e+000  1.095047192e+001  1.101923694e+001  8.3e-009 0.78  \n",
      "43  2.0e-005 2.8e-002 1.6e-003 1.00e+000  1.095502975e+001  1.101691376e+001  7.4e-009 0.80  \n",
      "44  1.8e-005 2.6e-002 1.5e-003 1.00e+000  1.095912734e+001  1.101481931e+001  6.7e-009 0.83  \n",
      "45  1.7e-005 2.5e-002 1.3e-003 1.00e+000  1.096281132e+001  1.101293114e+001  6.0e-009 0.88  \n",
      "46  1.5e-005 2.3e-002 1.2e-003 1.00e+000  1.096612349e+001  1.101122895e+001  5.4e-009 0.89  \n",
      "47  1.3e-005 2.2e-002 1.1e-003 1.00e+000  1.096910136e+001  1.100969434e+001  4.9e-009 0.91  \n",
      "48  7.2e-006 1.2e-002 5.8e-004 1.00e+000  1.098143165e+001  1.100324618e+001  2.6e-009 0.92  \n",
      "49  3.1e-006 5.1e-003 2.5e-004 1.00e+000  1.098948931e+001  1.099900703e+001  1.1e-009 0.94  \n",
      "50  2.8e-006 4.6e-003 2.3e-004 1.00e+000  1.099012874e+001  1.099869518e+001  1.0e-009 0.95  \n",
      "51  1.1e-006 1.8e-003 9.0e-005 1.00e+000  1.099348141e+001  1.099688356e+001  4.1e-010 0.97  \n",
      "52  1.0e-006 1.7e-003 8.1e-005 1.00e+000  1.099371040e+001  1.099677238e+001  3.7e-010 0.98  \n",
      "53  3.6e-007 6.0e-004 2.9e-005 1.00e+000  1.099497471e+001  1.099608269e+001  1.3e-010 1.00  \n",
      "54  3.3e-007 5.4e-004 2.6e-005 1.00e+000  1.099504775e+001  1.099604499e+001  1.2e-010 1.02  \n",
      "55  1.2e-007 2.0e-004 1.0e-005 1.00e+000  1.099544671e+001  1.099582648e+001  4.6e-011 1.03  \n",
      "56  1.1e-007 1.8e-004 9.1e-006 1.00e+000  1.099547141e+001  1.099581323e+001  4.1e-011 1.05  \n",
      "57  1.0e-007 1.7e-004 8.2e-006 1.00e+000  1.099549345e+001  1.099580112e+001  3.7e-011 1.05  \n",
      "58  9.1e-008 1.5e-004 7.4e-006 9.98e-001  1.099551332e+001  1.099579020e+001  3.3e-011 1.06  \n",
      "59  8.2e-008 1.3e-004 6.6e-006 9.99e-001  1.099553120e+001  1.099578037e+001  3.0e-011 1.08  \n",
      "60  7.4e-008 1.2e-004 6.0e-006 9.97e-001  1.099554729e+001  1.099577152e+001  2.7e-011 1.11  \n",
      "61  1.9e-008 3.0e-005 1.5e-006 1.00e+000  1.099565609e+001  1.099571139e+001  6.6e-012 1.13  \n",
      "62  2.4e-008 2.7e-005 1.3e-006 1.03e+000  1.099566029e+001  1.099570880e+001  6.1e-012 1.14  \n",
      "63  2.1e-008 2.4e-005 1.2e-006 9.43e-001  1.099566344e+001  1.099570717e+001  5.4e-012 1.16  \n",
      "64  1.9e-008 5.0e-006 2.5e-007 9.76e-001  1.099568612e+001  1.099569534e+001  1.2e-012 1.17  \n",
      "Interior-point optimizer terminated. Time: 1.17. \n",
      "\n",
      "Optimizer terminated. Time: 1.24    \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0995686116e+001   nrm: 2e+001   Viol.  con: 6e-007   var: 0e+000 \n",
      "  Dual.    obj: 1.0995695345e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 3e-005 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0995686116e+001   nrm: 2e+001   Viol.  con: 6e-007   var: 0e+000 \n",
      "  Dual.    obj: 1.0995695345e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 3e-005 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 5.9616407933e+004\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmpazzfbw\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n",
      "Solving took 2.01 seconds.\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "result packing took 78% of solve time\n",
      "solution checking took 50% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmpgvh5es\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (269) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (270) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.01            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.13    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6439              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.09              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.05            \n",
      "Factor     - nonzeros before factor : 2.66e+004         after factor           : 6.55e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : -1924             GP saved flops         : 6.58e+004       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.324836775e+005 3.796372382e+002  1.0e+000 0.23  \n",
      "1   2.7e+003 3.2e+003 1.8e+005 -9.70e-001 -2.296729475e+005 2.095107939e+003  7.9e-001 0.33  \n",
      "2   1.4e+003 1.7e+003 9.8e+004 -9.60e-001 -2.191546722e+005 8.134280765e+003  4.2e-001 0.42  \n",
      "3   4.0e+002 4.9e+002 2.8e+004 -9.18e-001 -1.759495008e+005 2.882105944e+004  1.2e-001 0.44  \n",
      "4   3.1e+002 3.7e+002 2.1e+004 -7.02e-001 -1.720926002e+005 2.170923330e+004  9.2e-002 0.45  \n",
      "5   9.9e+001 1.2e+002 6.9e+003 -6.08e-001 -1.111380848e+005 2.483003565e+004  3.0e-002 0.47  \n",
      "6   5.5e+001 6.7e+001 3.8e+003 -9.29e-002 -7.854907344e+004 2.051334981e+004  1.7e-002 0.48  \n",
      "7   3.3e+001 4.0e+001 2.3e+003 2.25e-001  -5.332067842e+004 1.618130788e+004  9.9e-003 0.50  \n",
      "8   1.4e+001 1.7e+001 1.0e+003 4.76e-001  -2.616624262e+004 9.184480383e+003  4.3e-003 0.63  \n",
      "9   5.7e+000 6.9e+000 3.9e+002 7.64e-001  -1.050074747e+004 4.459344380e+003  1.7e-003 0.81  \n",
      "10  2.3e+000 2.8e+000 1.6e+002 9.23e-001  -4.250974127e+003 1.968920554e+003  7.0e-004 0.95  \n",
      "11  1.7e+000 2.1e+000 1.2e+002 9.81e-001  -3.173067914e+003 1.409069614e+003  5.2e-004 1.20  \n",
      "12  7.4e-001 9.0e-001 5.2e+001 9.87e-001  -1.382869928e+003 6.286671336e+002  2.3e-004 1.50  \n",
      "13  5.7e-001 8.2e-001 4.0e+001 9.82e-001  -1.077276106e+003 4.853235744e+002  1.7e-004 1.72  \n",
      "14  3.8e-001 6.2e-001 2.7e+001 9.70e-001  -7.182537471e+002 3.258487011e+002  1.2e-004 1.84  \n",
      "15  1.5e-001 2.7e-001 1.1e+001 9.89e-001  -2.909161033e+002 1.307815246e+002  4.7e-005 1.92  \n",
      "16  1.1e-001 2.0e-001 7.7e+000 1.01e+000  -2.052274502e+002 9.857876761e+001  3.4e-005 2.13  \n",
      "17  5.3e-002 1.3e-001 3.8e+000 1.00e+000  -9.712001303e+001 5.033491804e+001  1.7e-005 2.22  \n",
      "18  5.0e-002 1.3e-001 3.6e+000 1.01e+000  -9.025274428e+001 5.044600720e+001  1.6e-005 2.28  \n",
      "19  2.8e-002 9.7e-002 2.0e+000 1.01e+000  -4.608214949e+001 3.170391474e+001  8.8e-006 2.34  \n",
      "20  2.1e-002 8.2e-002 1.5e+000 1.01e+000  -3.297916517e+001 2.613333449e+001  6.7e-006 2.53  \n",
      "21  1.2e-002 7.1e-002 8.9e-001 1.01e+000  -1.553634664e+001 1.924769736e+001  4.0e-006 2.61  \n",
      "22  1.1e-002 6.5e-002 8.3e-001 1.02e+000  -1.328242240e+001 1.884051234e+001  3.7e-006 2.66  \n",
      "23  3.7e-003 7.9e-002 2.7e-001 1.02e+000  3.338574528e+000  1.378548965e+001  1.2e-006 2.73  \n",
      "24  1.6e-003 8.2e-002 1.2e-001 1.02e+000  7.642097283e+000  1.215546428e+001  5.3e-007 2.95  \n",
      "25  1.5e-003 9.2e-002 1.1e-001 1.01e+000  7.893807521e+000  1.209547452e+001  4.9e-007 3.08  \n",
      "26  6.6e-004 9.5e-002 4.9e-002 1.01e+000  9.556775714e+000  1.142183848e+001  2.2e-007 3.19  \n",
      "27  6.2e-004 9.3e-002 4.6e-002 1.00e+000  9.612266323e+000  1.137567382e+001  2.1e-007 3.31  \n",
      "28  5.0e-004 7.9e-002 3.7e-002 9.71e-001  9.851675998e+000  1.126630994e+001  1.7e-007 3.53  \n",
      "29  4.5e-004 7.3e-002 3.4e-002 9.66e-001  9.948104258e+000  1.122402299e+001  1.5e-007 3.64  \n",
      "30  4.1e-004 6.6e-002 3.0e-002 9.72e-001  1.003689057e+001  1.118783013e+001  1.4e-007 3.77  \n",
      "31  3.7e-004 6.0e-002 2.7e-002 9.86e-001  1.012022804e+001  1.115838048e+001  1.2e-007 4.00  \n",
      "32  3.3e-004 5.5e-002 2.5e-002 9.99e-001  1.019540278e+001  1.113032693e+001  1.1e-007 4.09  \n",
      "33  3.0e-004 5.0e-002 2.2e-002 1.00e+000  1.026253667e+001  1.110395316e+001  9.9e-008 4.28  \n",
      "34  2.7e-004 4.6e-002 2.0e-002 1.01e+000  1.032203412e+001  1.107913347e+001  8.9e-008 4.81  \n",
      "35  2.4e-004 4.2e-002 1.8e-002 1.01e+000  1.037494242e+001  1.105615998e+001  8.0e-008 5.09  \n",
      "36  2.2e-004 3.9e-002 1.6e-002 1.01e+000  1.042213972e+001  1.103510100e+001  7.2e-008 5.17  \n",
      "37  1.9e-004 3.6e-002 1.4e-002 1.01e+000  1.046435342e+001  1.101591447e+001  6.5e-008 5.30  \n",
      "38  1.7e-004 3.3e-002 1.3e-002 1.01e+000  1.050216396e+001  1.099848663e+001  5.9e-008 5.58  \n",
      "39  1.6e-004 3.1e-002 1.2e-002 1.00e+000  1.053605600e+001  1.098268029e+001  5.3e-008 5.97  \n",
      "40  1.4e-004 2.9e-002 1.1e-002 1.00e+000  1.056644841e+001  1.096835678e+001  4.7e-008 6.14  \n",
      "41  1.3e-004 2.7e-002 9.5e-003 1.00e+000  1.059371015e+001  1.095538435e+001  4.3e-008 6.30  \n",
      "42  1.1e-004 2.6e-002 8.6e-003 1.00e+000  1.061816909e+001  1.094364080e+001  3.8e-008 6.41  \n",
      "43  1.0e-004 2.4e-002 7.7e-003 1.00e+000  1.064011760e+001  1.093301381e+001  3.5e-008 6.52  \n",
      "44  9.3e-005 2.3e-002 6.9e-003 1.00e+000  1.065981676e+001  1.092340047e+001  3.1e-008 6.64  \n",
      "45  8.4e-005 2.1e-002 6.2e-003 1.00e+000  1.067749994e+001  1.091470687e+001  2.8e-008 6.86  \n",
      "46  7.5e-005 2.0e-002 5.6e-003 1.00e+000  1.069337588e+001  1.090684731e+001  2.5e-008 7.11  \n",
      "47  6.8e-005 1.9e-002 5.1e-003 1.00e+000  1.070763134e+001  1.089974375e+001  2.3e-008 7.95  \n",
      "48  6.1e-005 1.9e-002 4.6e-003 1.00e+000  1.072043355e+001  1.089332521e+001  2.0e-008 8.50  \n",
      "49  5.5e-005 1.8e-002 4.1e-003 1.00e+000  1.073193223e+001  1.088752714e+001  1.8e-008 8.77  \n",
      "50  4.9e-005 1.7e-002 3.7e-003 1.00e+000  1.074226152e+001  1.088229089e+001  1.7e-008 8.84  \n",
      "51  4.4e-005 1.6e-002 3.3e-003 1.00e+000  1.075154155e+001  1.087756318e+001  1.5e-008 8.95  \n",
      "52  4.0e-005 1.6e-002 3.0e-003 1.00e+000  1.075987999e+001  1.087329564e+001  1.3e-008 9.14  \n",
      "53  3.6e-005 1.5e-002 2.7e-003 1.00e+000  1.076737330e+001  1.086944436e+001  1.2e-008 9.28  \n",
      "54  3.2e-005 1.5e-002 2.4e-003 1.00e+000  1.077410791e+001  1.086596949e+001  1.1e-008 9.38  \n",
      "55  2.9e-005 1.5e-002 2.2e-003 1.00e+000  1.078016130e+001  1.086283485e+001  9.8e-009 9.47  \n",
      "56  2.6e-005 1.4e-002 2.0e-003 1.00e+000  1.078560294e+001  1.086000767e+001  8.8e-009 9.58  \n",
      "57  2.4e-005 1.4e-002 1.8e-003 1.00e+000  1.079049510e+001  1.085745822e+001  7.9e-009 9.61  \n",
      "58  2.1e-005 1.4e-002 1.6e-003 1.00e+000  1.079489362e+001  1.085515956e+001  7.1e-009 9.84  \n",
      "59  1.9e-005 1.3e-002 1.4e-003 1.00e+000  1.079884861e+001  1.085308729e+001  6.4e-009 9.91  \n",
      "60  1.7e-005 1.3e-002 1.3e-003 1.00e+000  1.080240503e+001  1.085121932e+001  5.8e-009 9.98  \n",
      "61  1.5e-005 1.3e-002 1.2e-003 1.00e+000  1.080560321e+001  1.084953568e+001  5.2e-009 10.08 \n",
      "62  1.4e-005 1.3e-002 1.0e-003 1.00e+000  1.080847936e+001  1.084801830e+001  4.7e-009 10.17 \n",
      "63  1.3e-005 1.2e-002 9.4e-004 1.00e+000  1.081106599e+001  1.084665084e+001  4.2e-009 10.44 \n",
      "64  1.1e-005 1.2e-002 8.4e-004 1.00e+000  1.081339228e+001  1.084541850e+001  3.8e-009 11.28 \n",
      "65  1.0e-005 1.2e-002 7.6e-004 1.00e+000  1.081548446e+001  1.084430794e+001  3.4e-009 11.86 \n",
      "66  9.1e-006 1.2e-002 6.8e-004 1.00e+000  1.081736603e+001  1.084330709e+001  3.1e-009 12.67 \n",
      "67  3.9e-006 5.1e-003 2.9e-004 1.00e+000  1.082697940e+001  1.083813279e+001  1.3e-009 13.11 \n",
      "68  1.3e-006 1.7e-003 9.9e-005 1.00e+000  1.083178256e+001  1.083552196e+001  4.4e-010 13.38 \n",
      "69  1.2e-006 1.5e-003 8.9e-005 1.00e+000  1.083203448e+001  1.083540002e+001  4.0e-010 13.83 \n",
      "70  4.4e-007 5.8e-004 3.3e-005 1.00e+000  1.083338382e+001  1.083465209e+001  1.5e-010 14.16 \n",
      "71  4.0e-007 5.2e-004 3.0e-005 1.00e+000  1.083346749e+001  1.083460895e+001  1.4e-010 14.38 \n",
      "72  1.4e-007 1.8e-004 1.0e-005 1.00e+000  1.083394562e+001  1.083434211e+001  4.7e-011 14.88 \n",
      "73  1.4e-007 1.6e-004 9.4e-006 1.00e+000  1.083397118e+001  1.083432911e+001  4.2e-011 15.58 \n",
      "74  1.2e-007 1.5e-004 8.5e-006 1.00e+000  1.083399405e+001  1.083431620e+001  3.8e-011 16.45 \n",
      "75  1.1e-007 1.3e-004 7.6e-006 9.99e-001  1.083401468e+001  1.083430462e+001  3.4e-011 16.84 \n",
      "76  1.0e-007 1.2e-004 6.9e-006 1.00e+000  1.083403324e+001  1.083429418e+001  3.1e-011 16.98 \n",
      "77  9.0e-008 1.1e-004 6.2e-006 1.00e+000  1.083404994e+001  1.083428479e+001  2.8e-011 17.31 \n",
      "78  8.1e-008 9.6e-005 5.6e-006 1.00e+000  1.083406498e+001  1.083427633e+001  2.5e-011 17.44 \n",
      "79  7.3e-008 8.6e-005 5.0e-006 1.00e+000  1.083407850e+001  1.083426872e+001  2.2e-011 17.78 \n",
      "80  6.6e-008 7.8e-005 4.5e-006 1.00e+000  1.083409068e+001  1.083426185e+001  2.0e-011 17.83 \n",
      "81  5.9e-008 7.0e-005 4.0e-006 9.99e-001  1.083410164e+001  1.083425568e+001  1.8e-011 18.44 \n",
      "82  5.3e-008 6.3e-005 3.6e-006 9.98e-001  1.083411149e+001  1.083425015e+001  1.6e-011 19.14 \n",
      "83  4.8e-008 5.7e-005 3.3e-006 9.99e-001  1.083412036e+001  1.083424517e+001  1.5e-011 19.73 \n",
      "84  4.3e-008 5.1e-005 3.0e-006 1.00e+000  1.083412834e+001  1.083424068e+001  1.3e-011 20.03 \n",
      "85  8.3e-009 9.7e-006 5.6e-007 1.00e+000  1.083418643e+001  1.083420787e+001  2.5e-012 20.30 \n",
      "86  8.3e-008 3.4e-006 1.9e-007 3.90e-001  1.083419497e+001  1.083420145e+001  5.8e-013 20.48 \n",
      "Interior-point optimizer terminated. Time: 20.48. \n",
      "\n",
      "Optimizer terminated. Time: 20.58   \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0834194971e+001   nrm: 2e+001   Viol.  con: 1e-006   var: 0e+000 \n",
      "  Dual.    obj: 1.0834201447e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 1e-005 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0834194971e+001   nrm: 2e+001   Viol.  con: 1e-006   var: 0e+000 \n",
      "  Dual.    obj: 1.0834201447e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 1e-005 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 5.0726055392e+004\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmpgvh5es\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Solving took 21.9 seconds.\n",
      "result packing took 14% of solve time\n",
      "solution checking took 4% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmp35wq2n\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (269) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (270) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.02            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.11    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6439              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.09              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.06            \n",
      "Factor     - nonzeros before factor : 2.66e+004         after factor           : 6.55e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : -1924             GP saved flops         : 6.58e+004       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.324595193e+005 3.796372382e+002  1.0e+000 0.23  \n",
      "1   2.7e+003 3.2e+003 1.8e+005 -9.70e-001 -2.296462086e+005 2.096778281e+003  7.9e-001 0.55  \n",
      "2   1.4e+003 1.7e+003 9.8e+004 -9.60e-001 -2.191175153e+005 8.142770571e+003  4.2e-001 0.58  \n",
      "3   4.0e+002 4.9e+002 2.8e+004 -9.18e-001 -1.758928237e+005 2.883861855e+004  1.2e-001 0.61  \n",
      "4   3.1e+002 3.7e+002 2.1e+004 -7.01e-001 -1.719911771e+005 2.176347931e+004  9.2e-002 0.64  \n",
      "5   9.7e+001 1.2e+002 6.7e+003 -6.08e-001 -1.099296402e+005 2.491214201e+004  2.9e-002 0.69  \n",
      "6   5.6e+001 6.7e+001 3.8e+003 -8.28e-002 -7.863283896e+004 2.067146582e+004  1.7e-002 0.72  \n",
      "7   3.2e+001 3.9e+001 2.2e+003 2.22e-001  -5.263991750e+004 1.610349703e+004  9.7e-003 0.77  \n",
      "8   1.4e+001 1.7e+001 9.8e+002 4.83e-001  -2.581898420e+004 9.147335992e+003  4.3e-003 0.81  \n",
      "9   6.2e+000 7.5e+000 4.3e+002 7.67e-001  -1.140231913e+004 4.814688570e+003  1.9e-003 0.86  \n",
      "10  2.3e+000 2.8e+000 1.6e+002 9.13e-001  -4.204654570e+003 1.909385517e+003  6.9e-004 0.91  \n",
      "11  1.7e+000 2.1e+000 1.2e+002 9.82e-001  -3.169504666e+003 1.389756857e+003  5.1e-004 0.94  \n",
      "12  7.4e-001 8.9e-001 5.1e+001 9.86e-001  -1.376058631e+003 6.198434509e+002  2.2e-004 0.98  \n",
      "13  5.5e-001 8.3e-001 3.8e+001 9.80e-001  -1.043765594e+003 4.654996046e+002  1.7e-004 1.03  \n",
      "14  4.2e-001 6.7e-001 2.9e+001 9.74e-001  -7.882781945e+002 3.607021792e+002  1.3e-004 1.13  \n",
      "15  2.1e-001 3.4e-001 1.5e+001 9.83e-001  -3.982051521e+002 1.766498625e+002  6.4e-005 1.16  \n",
      "16  1.4e-001 2.3e-001 9.5e+000 1.00e+000  -2.545447386e+002 1.211248026e+002  4.2e-005 1.20  \n",
      "17  5.8e-002 1.6e-001 4.1e+000 1.00e+000  -1.081350560e+002 5.466260547e+001  1.8e-005 1.28  \n",
      "18  5.5e-002 1.5e-001 4.0e+000 1.01e+000  -1.014542476e+002 5.407424141e+001  1.8e-005 1.34  \n",
      "19  3.2e-002 1.1e-001 2.3e+000 1.01e+000  -5.403547268e+001 3.454607766e+001  1.0e-005 1.53  \n",
      "20  2.7e-002 9.5e-002 2.0e+000 1.01e+000  -4.549803456e+001 3.097264566e+001  8.7e-006 1.59  \n",
      "21  1.5e-002 7.9e-002 1.1e+000 1.01e+000  -2.160055388e+001 2.143464499e+001  4.9e-006 1.66  \n",
      "22  1.3e-002 6.6e-002 9.4e-001 1.02e+000  -1.640681072e+001 2.012529827e+001  4.2e-006 1.70  \n",
      "23  2.8e-003 1.4e-001 2.1e-001 1.01e+000  5.022113715e+000  1.292716643e+001  9.1e-007 1.75  \n",
      "24  1.6e-003 9.3e-002 1.2e-001 1.01e+000  7.571774253e+000  1.206866672e+001  5.2e-007 1.78  \n",
      "25  1.4e-003 9.8e-002 1.1e-001 1.01e+000  7.879889525e+000  1.199956034e+001  4.8e-007 1.80  \n",
      "26  7.3e-004 9.2e-002 5.5e-002 1.01e+000  9.345391835e+000  1.146045506e+001  2.5e-007 1.83  \n",
      "27  6.9e-004 8.9e-002 5.2e-002 9.99e-001  9.427785260e+000  1.139844083e+001  2.3e-007 1.84  \n",
      "28  6.3e-004 8.3e-002 4.8e-002 9.55e-001  9.548749341e+000  1.134270220e+001  2.1e-007 1.88  \n",
      "29  3.2e-004 7.8e-002 2.5e-002 9.27e-001  1.015749744e+001  1.108623214e+001  1.1e-007 1.91  \n",
      "30  2.9e-004 7.0e-002 2.2e-002 9.63e-001  1.023559685e+001  1.107819882e+001  9.9e-008 1.95  \n",
      "31  2.6e-004 6.4e-002 2.0e-002 1.01e+000  1.029491823e+001  1.105261246e+001  8.9e-008 2.00  \n",
      "32  2.4e-004 5.9e-002 1.8e-002 1.01e+000  1.034857452e+001  1.103021620e+001  8.0e-008 2.02  \n",
      "33  2.1e-004 5.4e-002 1.6e-002 1.01e+000  1.039570796e+001  1.100899137e+001  7.2e-008 2.05  \n",
      "34  1.9e-004 5.0e-002 1.5e-002 1.01e+000  1.043799045e+001  1.098978712e+001  6.5e-008 2.06  \n",
      "35  1.7e-004 4.6e-002 1.3e-002 1.01e+000  1.047586464e+001  1.097235213e+001  5.9e-008 2.09  \n",
      "36  1.5e-004 4.2e-002 1.2e-002 1.01e+000  1.050981511e+001  1.095654790e+001  5.3e-008 2.13  \n",
      "37  1.4e-004 3.9e-002 1.1e-002 1.01e+000  1.054025427e+001  1.094222718e+001  4.7e-008 2.14  \n",
      "38  1.3e-004 3.6e-002 9.5e-003 1.01e+000  1.056755255e+001  1.092925755e+001  4.3e-008 2.19  \n",
      "39  1.1e-004 3.4e-002 8.6e-003 1.01e+000  1.059203944e+001  1.091751640e+001  3.8e-008 2.22  \n",
      "40  1.0e-004 3.1e-002 7.7e-003 1.00e+000  1.061400899e+001  1.090689139e+001  3.5e-008 2.27  \n",
      "41  9.1e-005 2.9e-002 6.9e-003 1.00e+000  1.063372361e+001  1.089727963e+001  3.1e-008 2.33  \n",
      "42  8.2e-005 2.8e-002 6.2e-003 1.00e+000  1.065141774e+001  1.088858711e+001  2.8e-008 2.36  \n",
      "43  7.4e-005 2.6e-002 5.6e-003 1.00e+000  1.066730099e+001  1.088072815e+001  2.5e-008 2.38  \n",
      "44  6.7e-005 2.4e-002 5.1e-003 1.00e+000  1.068156084e+001  1.087362474e+001  2.3e-008 2.41  \n",
      "45  6.0e-005 2.3e-002 4.6e-003 1.00e+000  1.069436503e+001  1.086720582e+001  2.0e-008 2.42  \n",
      "46  5.4e-005 2.2e-002 4.1e-003 1.00e+000  1.070586374e+001  1.086140685e+001  1.8e-008 2.45  \n",
      "47  4.9e-005 2.1e-002 3.7e-003 1.00e+000  1.071619137e+001  1.085616915e+001  1.7e-008 2.47  \n",
      "48  4.4e-005 2.0e-002 3.3e-003 1.00e+000  1.072546830e+001  1.085143935e+001  1.5e-008 2.52  \n",
      "49  3.9e-005 1.9e-002 3.0e-003 1.00e+000  1.073380237e+001  1.084716908e+001  1.3e-008 2.56  \n",
      "50  3.5e-005 1.8e-002 2.7e-003 1.00e+000  1.074129024e+001  1.084331443e+001  1.2e-008 2.59  \n",
      "51  3.2e-005 1.7e-002 2.4e-003 1.00e+000  1.074801854e+001  1.083983561e+001  1.1e-008 2.64  \n",
      "52  2.9e-005 1.7e-002 2.2e-003 1.00e+000  1.075406500e+001  1.083669658e+001  9.8e-009 2.67  \n",
      "53  2.6e-005 1.6e-002 2.0e-003 1.00e+000  1.075949928e+001  1.083386471e+001  8.8e-009 2.69  \n",
      "54  2.3e-005 1.6e-002 1.8e-003 1.00e+000  1.076438389e+001  1.083131038e+001  7.9e-009 2.72  \n",
      "55  2.1e-005 1.5e-002 1.6e-003 1.00e+000  1.076877487e+001  1.082900678e+001  7.1e-009 2.73  \n",
      "56  1.9e-005 1.5e-002 1.4e-003 1.00e+000  1.077272247e+001  1.082692966e+001  6.4e-009 2.77  \n",
      "57  1.7e-005 1.4e-002 1.3e-003 1.00e+000  1.077627176e+001  1.082505702e+001  5.8e-009 2.80  \n",
      "58  1.5e-005 1.4e-002 1.2e-003 1.00e+000  1.077946316e+001  1.082336897e+001  5.2e-009 2.81  \n",
      "59  1.4e-005 1.4e-002 1.0e-003 1.00e+000  1.078233295e+001  1.082184744e+001  4.7e-009 2.86  \n",
      "60  1.2e-005 1.3e-002 9.4e-004 1.00e+000  1.078491367e+001  1.082047614e+001  4.2e-009 2.91  \n",
      "61  1.1e-005 1.3e-002 8.4e-004 1.00e+000  1.078723453e+001  1.081924030e+001  3.8e-009 2.94  \n",
      "62  1.0e-005 1.3e-002 7.6e-004 1.00e+000  1.078932177e+001  1.081812663e+001  3.4e-009 2.98  \n",
      "63  9.0e-006 1.3e-002 6.8e-004 1.00e+000  1.079119891e+001  1.081712303e+001  3.1e-009 3.02  \n",
      "64  8.1e-006 1.2e-002 6.2e-004 1.00e+000  1.079288710e+001  1.081621862e+001  2.8e-009 3.08  \n",
      "65  7.3e-006 1.2e-002 5.5e-004 1.00e+000  1.079440531e+001  1.081540352e+001  2.5e-009 3.09  \n",
      "66  6.6e-006 1.2e-002 5.0e-004 1.00e+000  1.079577054e+001  1.081466884e+001  2.2e-009 3.11  \n",
      "67  5.9e-006 1.2e-002 4.5e-004 1.00e+000  1.079699814e+001  1.081400653e+001  2.0e-009 3.14  \n",
      "68  5.3e-006 1.2e-002 4.0e-004 1.00e+000  1.079810197e+001  1.081340945e+001  1.8e-009 3.17  \n",
      "69  2.8e-006 6.2e-003 2.1e-004 1.00e+000  1.080278264e+001  1.081086036e+001  9.6e-010 3.19  \n",
      "70  1.3e-006 2.8e-003 9.7e-005 1.00e+000  1.080562738e+001  1.080929785e+001  4.4e-010 3.22  \n",
      "71  1.1e-006 2.5e-003 8.7e-005 1.00e+000  1.080587255e+001  1.080917610e+001  3.9e-010 3.25  \n",
      "72  4.4e-007 9.8e-004 3.4e-005 1.00e+000  1.080717655e+001  1.080845000e+001  1.5e-010 3.30  \n",
      "73  4.0e-007 8.8e-004 3.0e-005 1.00e+000  1.080726036e+001  1.080840649e+001  1.4e-010 3.36  \n",
      "74  1.4e-007 3.1e-004 1.1e-005 1.00e+000  1.080773896e+001  1.080813832e+001  4.7e-011 3.42  \n",
      "75  1.2e-007 2.8e-004 9.5e-006 1.00e+000  1.080776491e+001  1.080812435e+001  4.3e-011 3.47  \n",
      "76  1.1e-007 2.5e-004 8.5e-006 9.99e-001  1.080778789e+001  1.080811142e+001  3.8e-011 3.50  \n",
      "77  1.0e-007 2.2e-004 7.7e-006 1.00e+000  1.080780862e+001  1.080809980e+001  3.5e-011 3.55  \n",
      "78  9.0e-008 2.0e-004 6.9e-006 1.00e+000  1.080782727e+001  1.080808933e+001  3.1e-011 3.58  \n",
      "79  8.1e-008 1.8e-004 6.2e-006 1.00e+000  1.080784405e+001  1.080807990e+001  2.8e-011 3.59  \n",
      "80  7.3e-008 1.6e-004 5.6e-006 1.00e+000  1.080785916e+001  1.080807141e+001  2.5e-011 3.64  \n",
      "81  6.6e-008 1.5e-004 5.0e-006 1.00e+000  1.080787275e+001  1.080806377e+001  2.3e-011 3.66  \n",
      "82  5.9e-008 1.3e-004 4.5e-006 9.99e-001  1.080788498e+001  1.080805690e+001  2.0e-011 3.67  \n",
      "83  5.3e-008 1.2e-004 4.1e-006 1.00e+000  1.080789599e+001  1.080805071e+001  1.8e-011 3.70  \n",
      "84  4.8e-008 1.1e-004 3.7e-006 1.00e+000  1.080790588e+001  1.080804517e+001  1.7e-011 3.73  \n",
      "85  4.3e-008 9.6e-005 3.3e-006 1.00e+000  1.080791480e+001  1.080804016e+001  1.5e-011 3.77  \n",
      "86  8.2e-009 1.8e-005 6.3e-007 9.99e-001  1.080797970e+001  1.080800358e+001  2.8e-012 3.81  \n",
      "87  7.5e-008 4.9e-006 1.7e-007 6.35e-001  1.080799056e+001  1.080799656e+001  6.1e-013 3.86  \n",
      "Interior-point optimizer terminated. Time: 3.88. \n",
      "\n",
      "Optimizer terminated. Time: 3.97    \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0807990558e+001   nrm: 2e+001   Viol.  con: 8e-007   var: 0e+000 \n",
      "  Dual.    obj: 1.0807996564e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 2e-005 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0807990558e+001   nrm: 2e+001   Viol.  con: 8e-007   var: 0e+000 \n",
      "  Dual.    obj: 1.0807996564e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 2e-005 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 4.9414073824e+004\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmp35wq2n\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Solving took 5.39 seconds.\n",
      "result packing took 2.7e+02% of solve time\n",
      "solution checking took 13% of solve time\n",
      "Using solver 'mosek_cli'\n",
      "Solving for 3127 variables.\n",
      "Reading 'c:\\users\\berk\\appdata\\local\\temp\\tmppfhpmn\\gpkit_mosek'\n",
      "Data setup for expopt begin.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (269) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (270) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (505) of matrix 'A'.\n",
      "MOSEK warning 710: #1 (nearly) zero elements are specified in sparse col '' (642) of matrix 'A'.\n",
      "Number of Hessian non-zeros: 3425\n",
      "Data setup for expopt end.\n",
      "* Solving exponential optimization problem on dual form. *\n",
      "* The following log information refers to the solution of the dual problem. *\n",
      "Problem\n",
      "  Name                   :                 \n",
      "  Objective sense        : max             \n",
      "  Type                   : GECO (general convex optimization problem)\n",
      "  Constraints            : 3128            \n",
      "  Cones                  : 0               \n",
      "  Scalar variables       : 11482           \n",
      "  Matrix variables       : 0               \n",
      "  Integer variables      : 0               \n",
      "\n",
      "Optimizer started.\n",
      "Interior-point optimizer started.\n",
      "Presolve started.\n",
      "Linear dependency checker started.\n",
      "Linear dependency checker terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 908\n",
      "Eliminator terminated.\n",
      "Eliminator started.\n",
      "Freed constraints in eliminator : 0\n",
      "Eliminator terminated.\n",
      "Eliminator - tries                  : 2                 time                   : 0.00            \n",
      "Lin. dep.  - tries                  : 1                 time                   : 0.01            \n",
      "Lin. dep.  - number                 : 0               \n",
      "Presolve terminated. Time: 0.17    \n",
      "Matrix reordering started.\n",
      "Local matrix reordering started.\n",
      "Local matrix reordering terminated.\n",
      "Matrix reordering terminated.\n",
      "Optimizer  - threads                : 2               \n",
      "Optimizer  - solved problem         : the primal      \n",
      "Optimizer  - Constraints            : 1494\n",
      "Optimizer  - Cones                  : 0\n",
      "Optimizer  - Scalar variables       : 6439              conic                  : 0               \n",
      "Optimizer  - Semi-definite variables: 0                 scalarized             : 0               \n",
      "Factor     - setup time             : 0.13              dense det. time        : 0.00            \n",
      "Factor     - ML order time          : 0.00              GP order time          : 0.06            \n",
      "Factor     - nonzeros before factor : 2.66e+004         after factor           : 6.55e+004       \n",
      "Factor     - dense dim.             : 0                 flops                  : 2.58e+006       \n",
      "Factor     - GP saved nzs           : -1924             GP saved flops         : 6.58e+004       \n",
      "ITE PFEAS    DFEAS    GFEAS    PRSTATUS   POBJ              DOBJ              MU       TIME  \n",
      "0   3.4e+003 4.1e+003 2.3e+005 0.00e+000  -2.324551169e+005 3.796372382e+002  1.0e+000 0.33  \n",
      "1   2.7e+003 3.2e+003 1.8e+005 -9.70e-001 -2.296419188e+005 2.096663031e+003  7.9e-001 1.25  \n",
      "2   1.4e+003 1.7e+003 9.8e+004 -9.60e-001 -2.190808579e+005 8.162552988e+003  4.2e-001 2.06  \n",
      "3   4.0e+002 4.9e+002 2.8e+004 -9.18e-001 -1.759026708e+005 2.882504059e+004  1.2e-001 2.30  \n",
      "4   3.1e+002 3.7e+002 2.1e+004 -7.02e-001 -1.719700078e+005 2.176102180e+004  9.2e-002 2.72  \n",
      "5   9.7e+001 1.2e+002 6.7e+003 -6.08e-001 -1.098271079e+005 2.490912619e+004  2.9e-002 3.14  \n",
      "6   5.6e+001 6.7e+001 3.8e+003 -8.18e-002 -7.868051997e+004 2.065879984e+004  1.7e-002 3.28  \n",
      "7   3.2e+001 3.9e+001 2.2e+003 2.22e-001  -5.253907845e+004 1.606742618e+004  9.7e-003 4.48  \n",
      "8   1.4e+001 1.7e+001 9.8e+002 4.84e-001  -2.568133564e+004 9.105327029e+003  4.2e-003 7.14  \n",
      "9   6.2e+000 7.5e+000 4.3e+002 7.69e-001  -1.131997463e+004 4.774817622e+003  1.8e-003 7.19  \n",
      "10  2.3e+000 2.8e+000 1.6e+002 9.14e-001  -4.307790016e+003 1.950137802e+003  7.0e-004 7.31  \n",
      "11  1.7e+000 2.0e+000 1.2e+002 9.81e-001  -3.170202414e+003 1.383800360e+003  5.1e-004 7.51  \n",
      "12  7.4e-001 8.9e-001 5.1e+001 9.86e-001  -1.377694336e+003 6.190013785e+002  2.2e-004 7.64  \n",
      "13  5.4e-001 8.3e-001 3.8e+001 9.79e-001  -1.029973156e+003 4.564556798e+002  1.6e-004 7.86  \n",
      "14  4.6e-001 7.1e-001 3.2e+001 9.78e-001  -8.665737841e+002 3.955458245e+002  1.4e-004 7.95  \n",
      "15  2.2e-001 3.6e-001 1.6e+001 9.79e-001  -4.334449999e+002 1.908940728e+002  6.9e-005 8.02  \n",
      "16  1.5e-001 2.5e-001 1.1e+001 1.00e+000  -2.858550281e+002 1.354605317e+002  4.7e-005 8.48  \n",
      "17  6.9e-002 1.5e-001 4.9e+000 1.00e+000  -1.287918626e+002 6.520060401e+001  2.2e-005 8.88  \n",
      "18  4.1e-002 1.2e-001 2.9e+000 1.01e+000  -7.386940845e+001 4.197688132e+001  1.3e-005 9.00  \n",
      "19  2.5e-002 1.6e-001 1.8e+000 1.01e+000  -4.022682642e+001 2.880714683e+001  7.8e-006 9.22  \n",
      "20  1.1e-002 1.8e-001 8.2e-001 1.01e+000  -1.368770802e+001 1.829409004e+001  3.7e-006 9.27  \n",
      "21  7.1e-003 1.0e-001 5.2e-001 1.01e+000  -3.638366211e+000 1.651440518e+001  2.3e-006 9.41  \n",
      "22  1.6e-003 1.5e-001 1.2e-001 1.00e+000  7.553156369e+000  1.217827147e+001  5.3e-007 9.66  \n",
      "23  1.4e-003 1.4e-001 1.1e-001 1.01e+000  7.944231129e+000  1.203197555e+001  4.7e-007 9.73  \n",
      "24  6.3e-004 1.1e-001 4.9e-002 1.01e+000  9.501887493e+000  1.138485200e+001  2.2e-007 9.75  \n",
      "25  3.5e-004 8.7e-002 2.8e-002 1.01e+000  1.006572056e+001  1.112603632e+001  1.2e-007 9.78  \n",
      "26  2.3e-004 7.2e-002 1.8e-002 1.01e+000  1.032867064e+001  1.101846550e+001  8.0e-008 9.80  \n",
      "27  2.1e-004 6.6e-002 1.6e-002 1.01e+000  1.037899814e+001  1.099995583e+001  7.2e-008 9.83  \n",
      "28  1.9e-004 6.0e-002 1.5e-002 1.01e+000  1.042179089e+001  1.098045030e+001  6.5e-008 9.84  \n",
      "29  1.7e-004 5.6e-002 1.3e-002 1.01e+000  1.046051791e+001  1.096315097e+001  5.9e-008 9.88  \n",
      "30  1.5e-004 5.1e-002 1.2e-002 1.01e+000  1.049513764e+001  1.094737069e+001  5.3e-008 9.91  \n",
      "31  1.4e-004 4.7e-002 1.1e-002 1.01e+000  1.052617516e+001  1.093307357e+001  4.7e-008 9.92  \n",
      "32  1.2e-004 4.3e-002 9.5e-003 1.01e+000  1.055400488e+001  1.092012146e+001  4.3e-008 9.97  \n",
      "33  1.1e-004 4.0e-002 8.6e-003 1.01e+000  1.057896822e+001  1.090839754e+001  3.8e-008 10.03 \n",
      "34  9.9e-005 3.7e-002 7.7e-003 1.01e+000  1.060136498e+001  1.089778922e+001  3.5e-008 10.05 \n",
      "35  8.9e-005 3.5e-002 7.0e-003 1.01e+000  1.062146332e+001  1.088819412e+001  3.1e-008 10.06 \n",
      "36  8.0e-005 3.2e-002 6.3e-003 1.01e+000  1.063950254e+001  1.087951842e+001  2.8e-008 10.11 \n",
      "37  7.2e-005 3.0e-002 5.6e-003 1.00e+000  1.065569675e+001  1.087167678e+001  2.5e-008 10.14 \n",
      "38  6.5e-005 2.8e-002 5.1e-003 1.00e+000  1.067023752e+001  1.086459157e+001  2.3e-008 10.16 \n",
      "39  5.8e-005 2.6e-002 4.6e-003 1.00e+000  1.068329627e+001  1.085819211e+001  2.0e-008 10.19 \n",
      "40  5.3e-005 2.5e-002 4.1e-003 1.00e+000  1.069502601e+001  1.085241375e+001  1.8e-008 10.22 \n",
      "41  4.7e-005 2.4e-002 3.7e-003 1.00e+000  1.070556261e+001  1.084719658e+001  1.7e-008 10.31 \n",
      "42  4.3e-005 2.2e-002 3.3e-003 1.00e+000  1.071502663e+001  1.084248507e+001  1.5e-008 10.39 \n",
      "43  3.8e-005 2.1e-002 3.0e-003 1.00e+000  1.072352657e+001  1.083822936e+001  1.3e-008 10.42 \n",
      "44  3.5e-005 2.0e-002 2.7e-003 1.00e+000  1.073116120e+001  1.083438579e+001  1.2e-008 10.45 \n",
      "45  3.1e-005 1.9e-002 2.4e-003 1.00e+000  1.073801971e+001  1.083091545e+001  1.1e-008 10.47 \n",
      "46  2.8e-005 1.8e-002 2.2e-003 1.00e+000  1.074418190e+001  1.082778296e+001  9.8e-009 10.48 \n",
      "47  2.5e-005 1.8e-002 2.0e-003 1.00e+000  1.074971927e+001  1.082495612e+001  8.8e-009 10.52 \n",
      "48  2.3e-005 1.7e-002 1.8e-003 1.00e+000  1.075469586e+001  1.082240573e+001  7.9e-009 10.53 \n",
      "49  2.0e-005 1.6e-002 1.6e-003 1.00e+000  1.075916904e+001  1.082010531e+001  7.1e-009 10.59 \n",
      "50  1.8e-005 1.6e-002 1.4e-003 1.00e+000  1.076319024e+001  1.081803081e+001  6.4e-009 10.67 \n",
      "51  1.7e-005 1.5e-002 1.3e-003 1.00e+000  1.076680557e+001  1.081616042e+001  5.8e-009 10.73 \n",
      "52  1.5e-005 1.5e-002 1.2e-003 1.00e+000  1.077005636e+001  1.081447442e+001  5.2e-009 10.84 \n",
      "53  1.3e-005 1.4e-002 1.0e-003 1.00e+000  1.077297971e+001  1.081295494e+001  4.7e-009 10.89 \n",
      "54  1.2e-005 1.4e-002 9.4e-004 1.00e+000  1.077560889e+001  1.081158581e+001  4.2e-009 11.00 \n",
      "55  1.1e-005 1.4e-002 8.5e-004 1.00e+000  1.077797375e+001  1.081035236e+001  3.8e-009 11.05 \n",
      "56  9.8e-006 1.3e-002 7.6e-004 1.00e+000  1.078010108e+001  1.080924133e+001  3.4e-009 11.11 \n",
      "57  8.8e-006 1.3e-002 6.9e-004 1.00e+000  1.078201489e+001  1.080824074e+001  3.1e-009 11.14 \n",
      "58  7.9e-006 1.3e-002 6.2e-004 1.00e+000  1.078373665e+001  1.080733964e+001  2.8e-009 11.20 \n",
      "59  7.1e-006 1.3e-002 5.6e-004 1.00e+000  1.078528559e+001  1.080652806e+001  2.5e-009 11.23 \n",
      "60  6.4e-006 1.2e-002 5.0e-004 1.00e+000  1.078667886e+001  1.080579694e+001  2.2e-009 11.27 \n",
      "61  5.8e-006 1.2e-002 4.5e-004 1.00e+000  1.078793188e+001  1.080513805e+001  2.0e-009 11.28 \n",
      "62  5.2e-006 1.2e-002 4.1e-004 1.00e+000  1.078905859e+001  1.080454407e+001  1.8e-009 11.42 \n",
      "63  4.7e-006 1.2e-002 3.6e-004 1.00e+000  1.079007168e+001  1.080400855e+001  1.6e-009 11.47 \n",
      "64  4.2e-006 1.2e-002 3.3e-004 1.00e+000  1.079098274e+001  1.080352588e+001  1.5e-009 11.53 \n",
      "65  3.8e-006 1.2e-002 3.0e-004 1.00e+000  1.079180222e+001  1.080309102e+001  1.3e-009 11.58 \n",
      "66  3.4e-006 1.2e-002 2.7e-004 1.00e+000  1.079253938e+001  1.080269928e+001  1.2e-009 11.61 \n",
      "67  3.1e-006 1.1e-002 2.4e-004 1.00e+000  1.079320250e+001  1.080234641e+001  1.1e-009 11.63 \n",
      "68  2.8e-006 1.1e-002 2.2e-004 1.00e+000  1.079379904e+001  1.080202855e+001  9.6e-010 11.67 \n",
      "69  2.5e-006 1.1e-002 1.9e-004 1.00e+000  1.079433569e+001  1.080174226e+001  8.7e-010 11.73 \n",
      "70  2.2e-006 1.1e-002 1.7e-004 1.00e+000  1.079481849e+001  1.080148440e+001  7.8e-010 11.75 \n",
      "71  2.0e-006 1.1e-002 1.6e-004 1.00e+000  1.079525285e+001  1.080125217e+001  7.0e-010 11.78 \n",
      "72  1.8e-006 1.1e-002 1.4e-004 1.00e+000  1.079564363e+001  1.080104302e+001  6.3e-010 11.80 \n",
      "73  1.6e-006 1.1e-002 1.3e-004 1.00e+000  1.079599520e+001  1.080085467e+001  5.7e-010 11.83 \n",
      "74  1.5e-006 1.1e-002 1.1e-004 1.00e+000  1.079631150e+001  1.080068503e+001  5.1e-010 11.86 \n",
      "75  1.3e-006 1.1e-002 1.0e-004 1.00e+000  1.079659606e+001  1.080053224e+001  4.6e-010 11.89 \n",
      "76  1.2e-006 1.1e-002 9.3e-005 1.00e+000  1.079685205e+001  1.080039461e+001  4.2e-010 11.94 \n",
      "77  1.1e-006 1.1e-002 8.3e-005 1.00e+000  1.079708232e+001  1.080027063e+001  3.7e-010 11.98 \n",
      "78  9.6e-007 1.1e-002 7.5e-005 1.00e+000  1.079728945e+001  1.080015894e+001  3.4e-010 12.05 \n",
      "79  8.6e-007 1.1e-002 6.8e-005 1.00e+000  1.079747574e+001  1.080005830e+001  3.0e-010 12.09 \n",
      "80  7.8e-007 1.0e-002 6.1e-005 1.00e+000  1.079764329e+001  1.079996760e+001  2.7e-010 12.14 \n",
      "81  7.0e-007 1.0e-002 5.5e-005 1.00e+000  1.079779398e+001  1.079988587e+001  2.5e-010 12.20 \n",
      "82  6.3e-007 1.0e-002 4.9e-005 1.00e+000  1.079792952e+001  1.079981221e+001  2.2e-010 12.28 \n",
      "83  5.7e-007 1.0e-002 4.4e-005 1.00e+000  1.079805143e+001  1.079974586e+001  2.0e-010 12.33 \n",
      "84  5.1e-007 1.0e-002 4.0e-005 1.00e+000  1.079816109e+001  1.079968610e+001  1.8e-010 12.36 \n",
      "85  4.6e-007 1.0e-002 3.6e-005 1.00e+000  1.079825975e+001  1.079963228e+001  1.6e-010 12.38 \n",
      "86  4.1e-007 1.0e-002 3.2e-005 1.00e+000  1.079834852e+001  1.079958379e+001  1.4e-010 12.47 \n",
      "87  3.7e-007 1.0e-002 2.9e-005 1.00e+000  1.079842839e+001  1.079954012e+001  1.3e-010 12.52 \n",
      "88  3.3e-007 1.0e-002 2.6e-005 1.00e+000  1.079850025e+001  1.079950083e+001  1.2e-010 12.56 \n",
      "89  3.0e-007 1.0e-002 2.4e-005 1.00e+000  1.079856492e+001  1.079946544e+001  1.1e-010 12.61 \n",
      "90  2.7e-007 1.0e-002 2.1e-005 1.00e+000  1.079862309e+001  1.079943364e+001  9.5e-011 12.66 \n",
      "91  2.4e-007 1.0e-002 1.9e-005 1.00e+000  1.079867545e+001  1.079940498e+001  8.6e-011 12.70 \n",
      "92  2.2e-007 1.0e-002 1.7e-005 1.00e+000  1.079872257e+001  1.079937915e+001  7.7e-011 12.75 \n",
      "93  2.0e-007 1.0e-002 1.5e-005 1.00e+000  1.079876497e+001  1.079935589e+001  6.9e-011 12.78 \n",
      "94  1.8e-007 1.0e-002 1.4e-005 1.00e+000  1.079880314e+001  1.079933493e+001  6.2e-011 12.83 \n",
      "95  1.6e-007 1.0e-002 1.3e-005 1.00e+000  1.079883748e+001  1.079931606e+001  5.6e-011 12.88 \n",
      "96  1.4e-007 1.0e-002 1.1e-005 1.00e+000  1.079886838e+001  1.079929910e+001  5.1e-011 12.91 \n",
      "97  1.3e-007 1.0e-002 1.0e-005 1.00e+000  1.079889618e+001  1.079928387e+001  4.5e-011 13.08 \n",
      "98  1.2e-007 1.0e-002 9.1e-006 1.00e+000  1.079892120e+001  1.079927014e+001  4.1e-011 13.13 \n",
      "99  1.1e-007 1.0e-002 8.2e-006 1.00e+000  1.079894371e+001  1.079925781e+001  3.7e-011 13.17 \n",
      "100 9.5e-008 1.0e-002 7.4e-006 1.00e+000  1.079896396e+001  1.079924670e+001  3.3e-011 13.28 \n",
      "101 8.5e-008 1.0e-002 6.7e-006 1.00e+000  1.079898220e+001  1.079923668e+001  3.0e-011 13.34 \n",
      "102 7.7e-008 1.0e-002 6.0e-006 1.00e+000  1.079899862e+001  1.079922764e+001  2.7e-011 13.38 \n",
      "103 6.9e-008 9.0e-003 5.4e-006 1.00e+000  1.079901339e+001  1.079921950e+001  2.4e-011 13.42 \n",
      "104 6.2e-008 8.1e-003 4.9e-006 9.99e-001  1.079902668e+001  1.079921219e+001  2.2e-011 13.45 \n",
      "105 5.6e-008 7.3e-003 4.4e-006 1.00e+000  1.079903864e+001  1.079920561e+001  2.0e-011 13.50 \n",
      "106 5.0e-008 6.5e-003 3.9e-006 9.99e-001  1.079904939e+001  1.079919974e+001  1.8e-011 13.53 \n",
      "107 4.5e-008 5.9e-003 3.5e-006 9.99e-001  1.079905908e+001  1.079919441e+001  1.6e-011 13.56 \n",
      "108 4.1e-008 5.3e-003 3.2e-006 9.98e-001  1.079906787e+001  1.079918932e+001  1.4e-011 13.64 \n",
      "109 3.7e-008 4.8e-003 2.9e-006 1.00e+000  1.079907572e+001  1.079918501e+001  1.3e-011 13.66 \n",
      "110 3.3e-008 4.3e-003 2.6e-006 1.00e+000  1.079908277e+001  1.079918114e+001  1.2e-011 13.75 \n",
      "111 6.3e-009 8.2e-004 4.9e-007 1.00e+000  1.079913416e+001  1.079915287e+001  2.2e-012 13.80 \n",
      "112 2.7e-009 4.6e-005 2.8e-008 9.96e-001  1.079914563e+001  1.079914669e+001  1.4e-013 13.83 \n",
      "Interior-point optimizer terminated. Time: 13.84. \n",
      "\n",
      "Optimizer terminated. Time: 13.95   \n",
      "solsta = 1, prosta = 1\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0799145628e+001   nrm: 2e+001   Viol.  con: 6e-008   var: 0e+000 \n",
      "  Dual.    obj: 1.0799146689e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 2e-004 \n",
      "* End solution on dual form. *\n",
      "Transforming to primal solution.\n",
      "\n",
      "Interior-point solution summary\n",
      "  Problem status  : PRIMAL_AND_DUAL_FEASIBLE\n",
      "  Solution status : OPTIMAL\n",
      "  Primal.  obj: 1.0799145628e+001   nrm: 2e+001   Viol.  con: 6e-008   var: 0e+000 \n",
      "  Dual.    obj: 1.0799146689e+001   nrm: 9e+002   Viol.  con: 0e+000   var: 2e-004 \n",
      "\n",
      "Expopt solution summary:\n",
      "PROBLEM STATUS      : PRIMAL_AND_DUAL_FEASIBLE\n",
      "Solution status     : OPTIMAL\n",
      "Primal - objective  : 4.8978937036e+004\n",
      "\n",
      "Writing solution file to - c:\\users\\berk\\appdata\\local\\temp\\tmppfhpmn\\gpkit_mosek.sol\n",
      "Return code: 0\n",
      "\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "Solving took 15.6 seconds.\n",
      "result packing took 14% of solve time\n",
      "solution checking took 3.9% of solve time\n",
      "Solving took 8 GP solves and 207 seconds.\n",
      "Warning: Constraint [W_{avg}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 0)*x_{CG}_Mission.1/CruiseSegment.1/Crui... >= 0.225*W_{ht}_Mission.1/Aircraft.1/HorizontalTail.1*x_{CG_{ht}}_Mission.1/Aircraft.1/HorizontalTail.1...] is not tight because the left hand side evaluated to 2825469.20772 force_pound * meter but the right hand side evaluated to 2725421.18554 force_pound * meter (Allowable error: 0.1%, Actual error: 3.7%)\n",
      "\n",
      "Warning: Constraint [W_{avg}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 1)*x_{CG}_Mission.1/CruiseSegment.1/Crui... >= 0.225*W_{ht}_Mission.1/Aircraft.1/HorizontalTail.1*x_{CG_{ht}}_Mission.1/Aircraft.1/HorizontalTail.1...] is not tight because the left hand side evaluated to 2825469.20772 force_pound * meter but the right hand side evaluated to 2725421.18554 force_pound * meter (Allowable error: 0.1%, Actual error: 3.7%)\n",
      "\n",
      "Warning: Constraint [W_{avg}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 0)*x_{CG}_Mission.1/CruiseSegment.1/Crui... >= 0.225*W_{ht}_Mission.1/Aircraft.1/HorizontalTail.1*x_{CG_{ht}}_Mission.1/Aircraft.1/HorizontalTail.1...] is not tight because the left hand side evaluated to 2586809.96294 force_pound * meter but the right hand side evaluated to 2526695.62062 force_pound * meter (Allowable error: 0.1%, Actual error: 2.4%)\n",
      "\n",
      "Warning: Constraint [W_{avg}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 1)*x_{CG}_Mission.1/CruiseSegment.1/Crui... >= 0.225*W_{ht}_Mission.1/Aircraft.1/HorizontalTail.1*x_{CG_{ht}}_Mission.1/Aircraft.1/HorizontalTail.1...] is not tight because the left hand side evaluated to 2586809.96294 force_pound * meter but the right hand side evaluated to 2526695.62062 force_pound * meter (Allowable error: 0.1%, Actual error: 2.4%)\n",
      "\n",
      "Warning: Constraint [\\Delta x_n_Mission.1/Aircraft.1/LandingGear.1 + x_n_Mission.1/Aircraft.1/LandingGear.1 [m]... >= x_{CG}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 0) [m]...] is not tight because the left hand side evaluated to 27.246996699 meter but the right hand side evaluated to 20.362907785 meter (Allowable error: 0.1%, Actual error: 25%)\n",
      "\n",
      "Warning: Constraint [\\Delta x_n_Mission.1/Aircraft.1/LandingGear.1 + x_n_Mission.1/Aircraft.1/LandingGear.1 [m]... >= x_{CG}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 1) [m]...] is not tight because the left hand side evaluated to 27.246996699 meter but the right hand side evaluated to 20.362907785 meter (Allowable error: 0.1%, Actual error: 25%)\n",
      "\n",
      "Warning: Constraint [F_{fuel}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 0)... >= 1e-07 + W_{burn}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 0)*W_{f_{primary}}_Mission.1/Ai...] is not tight because the left hand side evaluated to 0.44757193749859153 but the right hand side evaluated to 0.4296859150641865 (Allowable error: 0.1%, Actual error: 4.2%)\n",
      "\n",
      "Warning: Constraint [F_{fuel}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 1)... >= 1e-07 + W_{burn}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 1)*W_{f_{primary}}_Mission.1/Ai...] is not tight because the left hand side evaluated to 0.44757193749859153 but the right hand side evaluated to 0.4296859150641865 (Allowable error: 0.1%, Actual error: 4.2%)\n",
      "\n",
      "Warning: Constraint [W_{pass}_Mission.1/Aircraft.1/Fuselage.1_(0,) [lbf]... >= W_{avg. pass}_Mission.1/Aircraft.1/Fuselage.1*n_{pass}_Mission.1/Aircraft.1/Fuselage.1_(0,) [lbf]...] is not tight because the left hand side evaluated to 32774.301617 force_pound but the right hand side evaluated to 32400.0096623 force_pound (Allowable error: 0.1%, Actual error: 1.2%)\n",
      "\n",
      "Warning: Constraint [W_{pass}_Mission.1/Aircraft.1/Fuselage.1_(1,) [lbf]... >= W_{avg. pass}_Mission.1/Aircraft.1/Fuselage.1*n_{pass}_Mission.1/Aircraft.1/Fuselage.1_(1,) [lbf]...] is not tight because the left hand side evaluated to 32774.301617 force_pound but the right hand side evaluated to 32400.0096623 force_pound (Allowable error: 0.1%, Actual error: 1.2%)\n",
      "\n",
      "Warning: Constraint [c_{l_{vt,EO}}_Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1... >= 0.318*A_{vt}_Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1**-1*C_{L_{vt,EO}}_Mission.1/...] is not tight because the left hand side evaluated to 0.4999999902799728 but the right hand side evaluated to 0.30449309927586177 (Allowable error: 0.1%, Actual error: 64%)\n",
      "\n",
      "Warning: Constraint [x_m_Mission.1/Aircraft.1/LandingGear.1 [m]... >= x_{wing}_Mission.1/Aircraft.1/Fuselage.1 [m]...] is not tight because the left hand side evaluated to 22.1929129184 meter but the right hand side evaluated to 20.9550569688 meter (Allowable error: 0.1%, Actual error: 5.9%)\n",
      "\n",
      "Warning: Constraint [D_{wm}_Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1 [N]... >= 0.5*A_{2}_Mission.1/Aircraft.1/Engine.1/Sizing.1*C_{D_{wm}}_Mission.1/Aircraft.1/VerticalTail.1/Vert...] is not tight because the left hand side evaluated to 8265.23960371 newton but the right hand side evaluated to 2877.74050817 kilogram * meter / second ** 2 (Allowable error: 0.1%, Actual error: 1.9e+02%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/ClimbSegment.1/ClimbP.1/Air... >= x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(0, 0) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0426673478 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/ClimbSegment.1/ClimbP.1/Air... >= x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(0, 1) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0426673478 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/ClimbSegment.1/ClimbP.1/Air... >= x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(1, 0) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0398901466 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/ClimbSegment.1/ClimbP.1/Air... >= x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(1, 1) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0398901466 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/ClimbSegment.1/ClimbP.1/Air... >= x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(2, 0) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0278816791 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/ClimbSegment.1/ClimbP.1/Air... >= x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(2, 1) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0278816791 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraf... >= SM_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(0, 0)...] is not tight because the left hand side evaluated to 0.42734512616679327 but the right hand side evaluated to 0.10982369189542661 (Allowable error: 0.1%, Actual error: 5.7%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraf... >= SM_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(0, 1)...] is not tight because the left hand side evaluated to 0.42734512616679327 but the right hand side evaluated to 0.10982369189542661 (Allowable error: 0.1%, Actual error: 5.7%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraf... >= SM_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(1, 0)...] is not tight because the left hand side evaluated to 0.42663858257052123 but the right hand side evaluated to 0.10975145167579813 (Allowable error: 0.1%, Actual error: 5.7%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraf... >= SM_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(1, 1)...] is not tight because the left hand side evaluated to 0.42663858257052123 but the right hand side evaluated to 0.10975145167579813 (Allowable error: 0.1%, Actual error: 5.7%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraf... >= SM_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(2, 0)...] is not tight because the left hand side evaluated to 0.4235835262497542 but the right hand side evaluated to 0.10944030918024496 (Allowable error: 0.1%, Actual error: 5.6%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraf... >= SM_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2_(2, 1)...] is not tight because the left hand side evaluated to 0.4235835262497542 but the right hand side evaluated to 0.10944030918024496 (Allowable error: 0.1%, Actual error: 5.6%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2_(0, 0)*C_{L}_Mi... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraft...] is not tight because the left hand side evaluated to 13.60877328773789 but the right hand side evaluated to 5.607842138523213 (Allowable error: 0.1%, Actual error: 59%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2_(0, 1)*C_{L}_Mi... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraft...] is not tight because the left hand side evaluated to 13.60877328773789 but the right hand side evaluated to 5.607842138523213 (Allowable error: 0.1%, Actual error: 59%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2_(1, 0)*C_{L}_Mi... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraft...] is not tight because the left hand side evaluated to 12.17093538967517 but the right hand side evaluated to 5.607135594926941 (Allowable error: 0.1%, Actual error: 54%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2_(1, 1)*C_{L}_Mi... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraft...] is not tight because the left hand side evaluated to 12.17093538967517 but the right hand side evaluated to 5.607135594926941 (Allowable error: 0.1%, Actual error: 54%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2_(2, 0)*C_{L}_Mi... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraft...] is not tight because the left hand side evaluated to 9.2828251824664 but the right hand side evaluated to 5.604080538606174 (Allowable error: 0.1%, Actual error: 40%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2_(2, 1)*C_{L}_Mi... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/ClimbSegment.1/ClimbP.1/Aircraft...] is not tight because the left hand side evaluated to 9.2828251824664 but the right hand side evaluated to 5.604080538606174 (Allowable error: 0.1%, Actual error: 40%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/CruiseSegment.1/CruiseP.1/A... >= x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 0) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0227718033 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/CruiseSegment.1/CruiseP.1/A... >= x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 1) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 22.0227718033 meter (Allowable error: 0.1%, Actual error: 3.5%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/CruiseSegment.1/CruiseP.1/A... >= x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 0) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 21.8440593221 meter (Allowable error: 0.1%, Actual error: 4.3%)\n",
      "\n",
      "Warning: Constraint [0.25*\\Delta x_{AC_{wing}}_Mission.1/Aircraft.1/Wing.1 + x_{NP}_Mission.1/CruiseSegment.1/CruiseP.1/A... >= x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 1) [m]...] is not tight because the left hand side evaluated to 22.8311573637 meter but the right hand side evaluated to 21.8440593221 meter (Allowable error: 0.1%, Actual error: 4.3%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/CruiseSegment.1/CruiseP.1/Aircr... >= SM_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 0)...] is not tight because the left hand side evaluated to 0.42228353037014976 but the right hand side evaluated to 0.10930927819307969 (Allowable error: 0.1%, Actual error: 5.6%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/CruiseSegment.1/CruiseP.1/Aircr... >= SM_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(0, 1)...] is not tight because the left hand side evaluated to 0.42228353037014976 but the right hand side evaluated to 0.10930927819307969 (Allowable error: 0.1%, Actual error: 5.6%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/CruiseSegment.1/CruiseP.1/Aircr... >= SM_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 0)...] is not tight because the left hand side evaluated to 0.48254052576866974 but the right hand side evaluated to 0.11523209120797004 (Allowable error: 0.1%, Actual error: 6.6%)\n",
      "\n",
      "Warning: Constraint [-mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{CG}_Mission.1/CruiseSegment.1/CruiseP.1/Aircr... >= SM_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3_(1, 1)...] is not tight because the left hand side evaluated to 0.48254052576866974 but the right hand side evaluated to 0.11523209120797004 (Allowable error: 0.1%, Actual error: 6.6%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/HorizontalTailPerformance.3_(0, 0)*C_{L}_... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/Aircra...] is not tight because the left hand side evaluated to 8.695492197592571 but the right hand side evaluated to 5.60278054272657 (Allowable error: 0.1%, Actual error: 36%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/HorizontalTailPerformance.3_(0, 1)*C_{L}_... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/Aircra...] is not tight because the left hand side evaluated to 8.69549219759257 but the right hand side evaluated to 5.60278054272657 (Allowable error: 0.1%, Actual error: 36%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/HorizontalTailPerformance.3_(1, 0)*C_{L}_... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/Aircra...] is not tight because the left hand side evaluated to 8.37452320769762 but the right hand side evaluated to 5.557314566790267 (Allowable error: 0.1%, Actual error: 34%)\n",
      "\n",
      "Warning: Constraint [C_{L_{ht}}_Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/HorizontalTailPerformance.3_(1, 1)*C_{L}_... >= mac_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1**-1*x_{AC}_Mission.1/CruiseSegment.1/CruiseP.1/Aircra...] is not tight because the left hand side evaluated to 8.37452320769762 but the right hand side evaluated to 5.557314566790267 (Allowable error: 0.1%, Actual error: 34%)\n",
      "\n"
     ]
    },
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "\n",
      "Solves with these variables bounded:\n",
      "   value near lower bound: CruiseAlt_Mission.1_(0,), CruiseAlt_Mission.1_(1,)\n",
      "   value near upper bound: M_{r_{out}}_Mission.1/Aircraft.1/HorizontalTail.1/WingBox.5, TotalTime_Mission.1_(1,), TotalTime_Mission.1_(0,), T_{t_{4.1_{max-Cruise}}}_Mission.1, A_{tri}_Mission.1/Aircraft.1/Wing.1/WingNoStruct.1, d_{nacelle}_Mission.1/Aircraft.1/LandingGear.1, \\alpha_{max}_Mission.1/Aircraft.1/Engine.1/Thrust.1\n",
      "\n",
      "Checking for relaxed constants...\n",
      "GP iteration 0 has relaxed constants\n",
      "\n",
      "Cost\n",
      "----\n",
      " 6.934e+89\n",
      "\n",
      "Free Variables\n",
      "--------------\n",
      "                   | Mission.1/Aircraft.1/Engine.1/Compressor.1/Relax.1\n",
      "           \\pi_{d} : 1.236                                                Diffuser Pressure Ratio\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Engine.1/EngineConstants.1/Relax.1\n",
      "       f_{BLI_{P}} : 1.236                                                BLI Stagnation Pressure Loss Ratio\n",
      "       f_{BLI_{V}} : 1.171                                                BLI Velocity Loss Ratio\n",
      "                 g : 6.808                                                Gravitational Acceleration\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Engine.1/Turbine.1/Relax.1\n",
      "        C_{p_{t2}} : 2.628                                                Cp Value for Combustion Products in LP Turbine\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Fuselage.1/Relax.1\n",
      "               SPR : 1.123                                                Number of seats per row\n",
      "          l_{nose} : 1.385                                                Nose length\n",
      "               p_s : 2.239                                                Seat pitch\n",
      "\n",
      "                   | Mission.1/Aircraft.1/LandingGear.1/Relax.1\n",
      "  \\tan(\\psi_{max}) : 1.28                                                 Upper bound on psi\n",
      "          h_{hold} : 1.009                                                Hold height\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Relax.1\n",
      "        D_{reduct} : 3.089                                                BLI Drag Reduction Factor\n",
      "f_{L_{total/wing}} : 3.539                                                Total lift as a percentage of wing lift\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Wing.1/WingNoStruct.1/Relax.1\n",
      "     \\cos(\\Lambda) : 1.022                                                Cosine of quarter-chord sweep angle\n",
      "     \\tan(\\Lambda) : 1.131                                                Tangent of quarter-chord sweep angle\n",
      "\n",
      "                   | Mission.1/ClimbSegment.1/FlightState.4/Atmosphere.4/Relax.1\n",
      "           L_{atm} : [ 1.27      1         1                              Temperature lapse rate\n",
      "                       1.27      1         1         ]\n",
      "\n",
      "                   | Mission.1/FlightState.3/Atmosphere.3/Relax.1\n",
      "           L_{atm} : [ 1.27      1         1         1         1          Temperature lapse rate\n",
      "                       1.27      1         1         1         1         ]\n",
      "\n",
      "                   | Mission.1/Relax.1\n",
      "      MaxClimbTime : 3.542                                                Total Time in Climb\n",
      "\n",
      "GP iteration 1 has relaxed constants\n",
      "\n",
      "Cost\n",
      "----\n",
      " 2.454e+19\n",
      "\n",
      "Free Variables\n",
      "--------------\n",
      "                   | Mission.1/Aircraft.1/Engine.1/Combustor.1/Relax.1\n",
      "         C_{p_{c}} : 1.292 Cp Value for Fuel/Air Mix in Combustor\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Engine.1/Compressor.1/Relax.1\n",
      "           \\pi_{d} : 1.206 Diffuser Pressure Ratio\n",
      "          \\pi_{fn} : 1.171 Fan Duct Pressure Loss Ratio\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Engine.1/EngineConstants.1/Relax.1\n",
      "       f_{BLI_{P}} : 1.206 BLI Stagnation Pressure Loss Ratio\n",
      "       f_{BLI_{V}} : 1.004 BLI Velocity Loss Ratio\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Engine.1/Turbine.1/Relax.1\n",
      "        C_{p_{t2}} : 1.033 Cp Value for Combustion Products in LP Turbine\n",
      "\n",
      "                   | Mission.1/Aircraft.1/LandingGear.1/Relax.1\n",
      "          h_{hold} : 1.019 Hold height\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Relax.1\n",
      "f_{L_{total/wing}} : 2.168 Total lift as a percentage of wing lift\n",
      "\n",
      "GP iteration 2 has relaxed constants\n",
      "\n",
      "Cost\n",
      "----\n",
      " 4.847e+09\n",
      "\n",
      "Free Variables\n",
      "--------------\n",
      "                   | Mission.1/Aircraft.1/Engine.1/Compressor.1/Relax.1\n",
      "           \\pi_{d} : 1.074 Diffuser Pressure Ratio\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Engine.1/EngineConstants.1/Relax.1\n",
      "       f_{BLI_{P}} : 1.074 BLI Stagnation Pressure Loss Ratio\n",
      "\n",
      "                   | Mission.1/Aircraft.1/LandingGear.1/Relax.1\n",
      "          h_{hold} : 1.01  Hold height\n",
      "\n",
      "                   | Mission.1/Aircraft.1/Relax.1\n",
      "f_{L_{total/wing}} : 1.422 Total lift as a percentage of wing lift\n",
      "\n",
      "GP iteration 3 has relaxed constants\n",
      "\n",
      "Cost\n",
      "----\n",
      " 1.237e+05\n",
      "\n",
      "Free Variables\n",
      "--------------\n",
      "            | Mission.1/Aircraft.1/Engine.1/Compressor.1/Relax.1\n",
      "    \\pi_{d} : 1.002 Diffuser Pressure Ratio\n",
      "\n",
      "            | Mission.1/Aircraft.1/Engine.1/EngineConstants.1/Relax.1\n",
      "f_{BLI_{P}} : 1.002 BLI Stagnation Pressure Loss Ratio\n",
      "\n"
     ]
    }
   ],
   "source": [
    "objective = 'W_{f_{total}}'\n",
    "fixedBPR = False\n",
    "pRatOpt = True\n",
    "mutategparg = False\n",
    "\n",
    "# User definitions\n",
    "Nclimb = 3\n",
    "Ncruise = 2\n",
    "Nmission = 2\n",
    "aircraft = 'optimalD8'\n",
    "\n",
    "m = Mission(Nclimb, Ncruise, objective, aircraft, Nmission)\n",
    "\n",
    "substitutions = get_optimal_D8_subs()\n",
    "\n",
    "if Nmission == 3:\n",
    "    substitutions.update({\n",
    "        'R_{req}': [3000.*units('nmi'), 2000.*units('nmi')],#,2500.*units('nmi')],\n",
    "        'n_{pass}': [180., 160.],#,140.],\n",
    "    })\n",
    "else:\n",
    "    substitutions.update({\n",
    "        'R_{req}': 3000.*units('nmi'),\n",
    "        'n_{pass}': 180.,\n",
    "    })\n",
    "\n",
    "if fixedBPR:\n",
    "    substitutions.update({\n",
    "        '\\\\alpha_{max}': 6.97,\n",
    "    })\n",
    "\n",
    "if pRatOpt:\n",
    "    #del substitutions['\\pi_{f_D}']\n",
    "    del substitutions['\\pi_{lc_D}']\n",
    "    del substitutions['\\pi_{hc_D}']\n",
    "\n",
    "m = Model(m.cost, BCS(m))\n",
    "m.substitutions.update(substitutions)\n",
    "\n",
    "m_relax = relaxed_constants(m, None, ['M_{takeoff}', '\\\\theta_{db}'])\n",
    "sol = m_relax.localsolve(verbosity=4, iteration_limit=200, reltol=0.01, mutategp=mutategparg, skipsweepfailures=True)\n",
    "post_process(sol)"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": []
  },
  {
   "cell_type": "code",
   "execution_count": 5,
   "metadata": {},
   "outputs": [
    {
     "name": "stdout",
     "output_type": "stream",
     "text": [
      "\n",
      "Cost\n",
      "----\n",
      " 4.898e+04 [lbf]\n",
      "\n",
      "Free Variables\n",
      "--------------\n",
      "                         | Mission.1\n",
      "              Fsafetyfac : 1                                                                   Safety factor on inital climb thrust\n",
      "            MaxClimbTime : 16                                                    [min]         Total Time in Climb\n",
      "            MinCruiseAlt : 3.848e+04                                             [ft]          Minimum Cruise Altitude\n",
      "               OPR_{max} : 35                                                                  Maximum Overall Pressure Ratio\n",
      "T_{t_{4.1_{max-Cruise}}} : 1e+30                                                 [K]           Max Cruise Turbine Inlet Temp\n",
      "        W_{f_{missions}} : 4.898e+04                                             [lbf]         Fuel burn across all missions\n",
      "               ClimbTime : [ 16        16       ]                                [min]         Total Time in Climb\n",
      "               CruiseAlt : [ 1e-30     1e-30    ]                                [ft]          Cruise Altitude [feet]\n",
      "                 R_{req} : [ 3e+03     3e+03    ]                                [nmi]         Required Cruise Range\n",
      "               TotalTime : [ 1e+30     1e+30    ]                                [hr]          Total Mission Time\n",
      "\n",
      "                         | Mission.1/Aircraft.1\n",
      "            A_{corecowl} : 1.291                                                 [m²]          Core Cowling Area\n",
      "                 A_{exh} : 5.058                                                 [m²]          Exhaust Area\n",
      "             A_{fancowl} : 2.529                                                 [m²]          Fan Cowling Area\n",
      "               A_{inlet} : 5.058                                                 [m²]          Inlet Area\n",
      "       BLI_{wakebenefit} : 0.02                                                                Wake Drag Reduction from BLI Wake Ingestion\n",
      "              C_{engsys} : 1                                                                   Engine System Weight Margin/Sens Factor\n",
      "              D_{reduct} : 0.9842                                                              BLI Drag Reduction Factor\n",
      "        D_{wakefraction} : 0.33                                                                Percent of Total Drag From Wake Dissipation\n",
      "                 M_{min} : 0.72                                                                Minimum Cruise Mach Number\n",
      "                SM_{min} : 0.05                                                                Minimum Static Margin\n",
      "             S_{nacelle} : 12.64                                                 [m²]          Nacelle Surface Area\n",
      "                  V_{mn} : 133.8                                                 [m/s]         Maneuvering speed\n",
      "                  V_{ne} : 143.9                                                 [m/s]         Never-exceed speed\n",
      "                W_{eadd} : 821.2                                                 [lbf]         Additional Engine System Weight\n",
      "              W_{engsys} : 1.086e+04                                             [lbf]         Total Engine System Weight\n",
      "              W_{hpesys} : 1450                                                  [lbf]         Power Systems Weight\n",
      "                W_{misc} : 5139                                                  [lbf]         Sum of Miscellaneous Weights\n",
      "             W_{nacelle} : 1313                                                  [lbf]         Nacelle Weight\n",
      "               W_{pylon} : 517.3                                                 [lbf]         Engine Pylon Weight\n",
      "          W_{total, max} : 1.45e+05                                              [lbf]         Total Aircraft Weight\n",
      "           \\Delta x_{CG} : 1.829                                                 [m]           Max CG Travel Range\n",
      "              \\rho_{T/O} : 1.225                                                 [kg/m³]       Air density at takeoff\n",
      "      f_{L_{total/wing}} : 1.195                                                               Total lift as a percentage of wing lift\n",
      "         f_{S_{nacelle}} : 0.09163                                                             Non-dimensional Nacelle Area\n",
      "                f_{eadd} : 0.1                                                                 Additional Engine Weight Fraction\n",
      "          f_{fuel_{res}} : 0.2                                                                 Fuel Reserve Fraction\n",
      "              f_{hpesys} : 0.01                                                                Power Systems Weight Fraction\n",
      "               f_{pylon} : 0.05                                                                Pylong Weight Fraction\n",
      "            f_{wingfuel} : 1                                                                   Fraction of fuel stored in wing tanks\n",
      "             l_{nacelle} : 1.474                                                 [m]           Nacelle Length\n",
      "               n_{aisle} : 2                                                                   Number of Aisles\n",
      "                 n_{eng} : 2                                                                   Number of Engines\n",
      "                  n_{vt} : 2                                                                   Number of Vertical Tails\n",
      "         r_{S_{nacelle}} : 6                                                                   Nacelle and Pylon Wetted Area\n",
      "         r_{v_{nacelle}} : 0.925                                                               Incoming Nacelle Velocity Ratio\n",
      "            x_{CG_{min}} : 17.07                                                 [m]           Maximum Forward CG\n",
      "                 x_{eng} : 31.27                                                 [m]           Engine x-location\n",
      "              x_{hpesys} : 9.723                                                 [m]           Power Systems Weight x-Location\n",
      "                x_{misc} : 2.744                                                 [m]           Misc Weight Centroid\n",
      "            I_{z_{fuse}} : [ 3.33e+06  3.33e+06 ]                                [kg·m²]       Fuselage moment of inertia\n",
      "            I_{z_{tail}} : [ 1.2e+06   1.2e+06  ]                                [kg·m²]       Tail moment of inertia\n",
      "            I_{z_{wing}} : [ 2.08e+06  2.08e+06 ]                                [kg·m²]       Wing moment of inertia\n",
      "                   I_{z} : [ 6.62e+06  6.62e+06 ]                                [kg·m²]       Aircraft Z-axis Moment of Inertia\n",
      "                    PRFC : [ 0.416     0.416    ]                                              Payload-Range Fuel Consumption\n",
      "                 W_{dry} : [ 8.18e+04  8.18e+04 ]                                [lbf]         Zero Fuel Aircraft Weight\n",
      "           W_{f_{climb}} : [ 2.25e+03  2.25e+03 ]                                [lbf]         Fuel Weight Burned in Climb\n",
      "          W_{f_{cruise}} : [ 1.82e+04  1.82e+04 ]                                [lbf]         Fuel Weight Burned in Cruise\n",
      "         W_{f_{primary}} : [ 2.04e+04  2.04e+04 ]                                [lbf]         Total Fuel Weight Less Fuel Reserves\n",
      "           W_{f_{total}} : [ 2.45e+04  2.45e+04 ]                                [lbf]         Total Fuel Weight\n",
      "               W_{total} : [ 1.45e+05  1.45e+05 ]                                [lbf]         Total Aircraft Weight\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1\n",
      "           HTR_{f_{SUB}} : 0.91                                                                1 - HTRf^2\n",
      "         HTR_{lpc_{SUB}} : 0.64                                                                1 - HTRlpc^2\n",
      "       T_{t_{4.1_{max}}} : 1567                                                  [K]           Max turbine inlet temperature\n",
      "              W_{engine} : 3.653e+04                                             [N]           Weight of a Single Turbofan Engine\n",
      "                 d_{LPC} : 0.3701                                                [m]           LPC Diameter\n",
      "                   d_{f} : 1.638                                                 [m]           Fan Diameter\n",
      "                F_{spec} : [ 4.45e+04  4.32e+04  2.6e+04   1.28e+04  1.19e+04    [N]           Specified Total Thrust\n",
      "                             4.45e+04  4.32e+04  2.6e+04   1.28e+04  1.19e+04  ]\n",
      "                     OPR : [ 20.7      35        35        14.6      16.2                      Overall Pressure Ratio\n",
      "                             20.7      35        35        14.6      16.2      ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Combustor.1\n",
      "               C_{p_{c}} : 1258                                                  [J/K/kg]      Cp Value for Fuel/Air Mix in Combustor\n",
      "             C_{p_{fuel} : 2010                                                  [J/K/kg]      Specific Heat Capacity of Kerosene (~Jet Fuel)\n",
      "                 T_{t_f} : 435                                                   [K]           Incoming Fuel Total Temperature\n",
      "                \\alpha_c : 0.16                                                                Total Cooling Flow Bypass Ratio\n",
      "                \\eta_{B} : 0.985                                                               Burner Efficiency\n",
      "                 \\pi_{b} : 0.94                                                                Burner Pressure Ratio\n",
      "                   h_{f} : 43                                                    [MJ/kg]       Heat of Combustion of Jet Fuel\n",
      "               hold_{4a} : 1.006                                                               1+(gamma-1)/2 * M_4a**2\n",
      "                  r_{uc} : 0.01                                                                User Specified Cooling Flow Velocity Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Combustor.1/Relax.1\n",
      "               C_{p_{c}} : 1                                                                   Cp Value for Fuel/Air Mix in Combustor\n",
      "             C_{p_{fuel} : 1                                                                   Specific Heat Capacity of Kerosene (~Jet Fuel)\n",
      "                 T_{t_f} : 1                                                                   Incoming Fuel Total Temperature\n",
      "                \\alpha_c : 1                                                                   Total Cooling Flow Bypass Ratio\n",
      "                \\eta_{B} : 1                                                                   Burner Efficiency\n",
      "                 \\pi_{b} : 1                                                                   Burner Pressure Ratio\n",
      "                   h_{f} : 1                                                                   Heat of Combustion of Jet Fuel\n",
      "               hold_{4a} : 1                                                                   1+(gamma-1)/2 * M_4a**2\n",
      "                  r_{uc} : 1                                                                   User Specified Cooling Flow Velocity Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Compressor.1\n",
      "                C_{p_{1} : 1008                                                  [J/K/kg]      Cp Value for Air at 350K\n",
      "                C_{p_{2} : 1099                                                  [J/K/kg]      Cp Value for Air at 800K\n",
      "              C_{p_{air} : 1003                                                  [J/K/kg]      Cp Value for Air at 250K\n",
      "            \\gamma_{air} : 1.4                                                                 Specific Heat Ratio for Ambient Air\n",
      "                 \\pi_{d} : 0.995                                                               Diffuser Pressure Ratio\n",
      "                \\pi_{fn} : 0.985                                                               Fan Duct Pressure Loss Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Compressor.1/Relax.1\n",
      "                C_{p_{1} : 1                                                                   Cp Value for Air at 350K\n",
      "                C_{p_{2} : 1                                                                   Cp Value for Air at 800K\n",
      "              C_{p_{air} : 1                                                                   Cp Value for Air at 250K\n",
      "            \\gamma_{air} : 1                                                                   Specific Heat Ratio for Ambient Air\n",
      "                 \\pi_{d} : 1                                                                   Diffuser Pressure Ratio\n",
      "                \\pi_{fn} : 1                                                                   Fan Duct Pressure Loss Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EngineConstants.1\n",
      "                 P_{ref} : 101.3                                                 [kPa]         Reference Stagnation Pressure\n",
      "                       R : 287                                                   [J/K/kg]      R\n",
      "                 T_{ref} : 288.1                                                 [K]           Reference Stagnation Temperature\n",
      "             f_{BLI_{P}} : 0.9627                                                              BLI Stagnation Pressure Loss Ratio\n",
      "             f_{BLI_{V}} : 0.9273                                                              BLI Velocity Loss Ratio\n",
      "                       g : 9.81                                                  [m/s²]        Gravitational Acceleration\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EngineConstants.1/Relax.1\n",
      "                 P_{ref} : 1                                                                   Reference Stagnation Pressure\n",
      "                       R : 1                                                                   R\n",
      "                 T_{ref} : 1                                                                   Reference Stagnation Temperature\n",
      "             f_{BLI_{P}} : 1                                                                   BLI Stagnation Pressure Loss Ratio\n",
      "             f_{BLI_{V}} : 1                                                                   BLI Velocity Loss Ratio\n",
      "                       g : 1                                                                   Gravitational Acceleration\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/CombustorPerformance.1\n",
      "                  M_{4a} : [ 0.103     0.103     0.103     0.103     0.103                     User Specified Station 4a Mach #\n",
      "                             0.103     0.103     0.103     0.103     0.103     ]\n",
      "                  P_{4a} : [ 1.59e+03  1.75e+03  987       385       374         [kPa]         Static Pressure at Station 4a (4a)\n",
      "                             1.59e+03  1.75e+03  987       385       374       ]\n",
      "                 P_{t_4} : [ 1.55e+03  1.71e+03  962       375       364         [kPa]         Stagnation Pressure at the Combustor Exit (4)\n",
      "                             1.55e+03  1.71e+03  962       375       364       ]\n",
      "             P_{t_{4.1}} : [ 1.59e+03  1.75e+03  987       385       374         [kPa]         Stagnation Pressure at the Turbine Inlet (4.1)\n",
      "                             1.59e+03  1.75e+03  987       385       374       ]\n",
      "                 T_{4.1} : [ 1.57e+03  1.57e+03  1.57e+03  1.42e+03  1.36e+03    [K]           Static Temperature at the Turbine Inlet (4.1)\n",
      "                             1.57e+03  1.57e+03  1.57e+03  1.42e+03  1.36e+03  ]\n",
      "                 T_{t_4} : [ 1.74e+03  1.73e+03  1.74e+03  1.6e+03   1.53e+03    [K]           Combustor Exit (Station 4) Stagnation Temperature\n",
      "                             1.74e+03  1.73e+03  1.74e+03  1.6e+03   1.53e+03  ]\n",
      "             T_{t_{4.1}} : [ 1.57e+03  1.57e+03  1.57e+03  1.42e+03  1.36e+03    [K]           Stagnation Temperature at the Turbine Inlet (4.1)\n",
      "                             1.57e+03  1.57e+03  1.57e+03  1.42e+03  1.36e+03  ]\n",
      "                       f : [ 0.03      0.0281    0.0303    0.0304    0.0282                    Fuel Air Mass Flow Fraction\n",
      "                             0.03      0.0281    0.0303    0.0304    0.0282    ]\n",
      "                     fp1 : [ 1.03      1.03      1.03      1.03      1.03                      f + 1\n",
      "                             1.03      1.03      1.03      1.03      1.03      ]\n",
      "                 h_{t_4} : [ 2.19e+06  2.18e+06  2.19e+06  2.02e+06  1.92e+06    [J/kg]        Stagnation Enthalpy at the Combustor Exit (4)\n",
      "                             2.19e+06  2.18e+06  2.19e+06  2.02e+06  1.92e+06  ]\n",
      "             h_{t_{4.1}} : [ 1.97e+06  1.97e+06  1.97e+06  1.79e+06  1.71e+06    [J/kg]        Stagnation Enthalpy at the Turbine Inlet (4.1)\n",
      "                             1.97e+06  1.97e+06  1.97e+06  1.79e+06  1.71e+06  ]\n",
      "                     u_c : [ 0.825     0.823     0.826     0.792     0.773       [m/s]         Cooling Airflow Speed at Station 4a\n",
      "                             0.825     0.823     0.826     0.792     0.773     ]\n",
      "                 u_{4.1} : [ 3.25      3.25      3.25      3.12      3.05        [m/s]         Flow Velocity at Station 4.1\n",
      "                             3.25      3.25      3.25      3.12      3.05      ]\n",
      "                  u_{4a} : [ 82.5      82.3      82.6      79.2      77.3        [m/s]         Flow Velocity at Station 4a\n",
      "                             82.5      82.3      82.6      79.2      77.3      ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/CompressorPerformance.1\n",
      "               P_{T_{2}} : [ 79.5      52        29.2      27.3      23.9        [kPa]         Stagnation Pressure at the Fan Inlet (2)\n",
      "                             79.5      52        29.2      27.3      23.9      ]\n",
      "                 P_{t_0} : [ 79.9      52.2      29.4      27.4      24          [kPa]         Free Stream Stagnation Pressure\n",
      "                             79.9      52.2      29.4      27.4      24        ]\n",
      "                 P_{t_3} : [ 1.65e+03  1.82e+03  1.02e+03  399       387         [kPa]         Stagnation Pressure at the HPC Exit (3)\n",
      "                             1.65e+03  1.82e+03  1.02e+03  399       387       ]\n",
      "                 P_{t_7} : [ 115       81.2      45.3      37        33.1        [kPa]         Stagnation Pressure at the Fan Nozzle Exit (7)\n",
      "                             115       81.2      45.3      37        33.1      ]\n",
      "             P_{t_{1.8}} : [ 79.5      52        29.2      27.3      23.9        [kPa]         Stagnation Pressure at the Diffuser Exit (1.8)\n",
      "                             79.5      52        29.2      27.3      23.9      ]\n",
      "             P_{t_{2.1}} : [ 117       82.4      46        37.6      33.6        [kPa]         Stagnation Pressure at the Fan Exit (2.1)\n",
      "                             117       82.4      46        37.6      33.6      ]\n",
      "             P_{t_{2.5}} : [ 176       205       108       37.6      37.7        [kPa]         Stagnation Pressure at the LPC Exit (2.5)\n",
      "                             176       205       108       37.6      37.7      ]\n",
      "               T_{T_{2}} : [ 285       266       239       234       228         [K]           Stagnation Temperature at the Fan Inlet (2)\n",
      "                             285       266       239       234       228       ]\n",
      "                 T_{t_0} : [ 285       266       239       234       228         [K]           Free Stream Stagnation Temperature\n",
      "                             285       266       239       234       228       ]\n",
      "                 T_{t_3} : [ 703       771       692       517       521         [K]           Stagnation Temperature at the HPC Exit (3)\n",
      "                             703       771       692       517       521       ]\n",
      "                 T_{t_7} : [ 322       308       276       259       254         [K]           Stagnation Temperature at the Fan Nozzle Exit (7)\n",
      "                             322       308       276       259       254       ]\n",
      "             T_{t_{1.8}} : [ 285       266       239       234       228         [K]           Stagnation Temperature at the Diffuser Exit (1.8)\n",
      "                             285       266       239       234       228       ]\n",
      "             T_{t_{2.1}} : [ 322       308       276       259       254         [K]           Stagnation Temperature at the Fan Exit (2.1)\n",
      "                             322       308       276       259       254       ]\n",
      "             T_{t_{2.5}} : [ 364       406       358       258       263         [K]           Stagnation Temperature at the LPC Exit (2.5)\n",
      "                             364       406       358       258       263       ]\n",
      "                 \\pi_{f} : [ 1.47      1.59      1.57      1.38      1.4                       Fan Pressure Ratio\n",
      "                             1.47      1.59      1.57      1.38      1.4       ]\n",
      "                \\pi_{hc} : [ 9.38      8.86      9.47      10.6      10.3                      HPC Pressure Ratio\n",
      "                             9.38      8.86      9.47      10.6      10.3      ]\n",
      "                \\pi_{lc} : [ 1.5       2.49      2.35      1         1.12                      LPC Pressure Ratio\n",
      "                             1.5       2.49      2.35      1         1.12      ]\n",
      "                      c1 : [ 1.08      1.12      1.13      1.1       1.1                       Constant in Stagnation Eqn\n",
      "                             1.08      1.12      1.13      1.1       1.1       ]\n",
      "               h_{T_{2}} : [ 2.86e+05  2.66e+05  2.39e+05  2.35e+05  2.29e+05    [J/kg]        Stagnation Enthalpy at the Fan Inlet (2)\n",
      "                             2.86e+05  2.66e+05  2.39e+05  2.35e+05  2.29e+05  ]\n",
      "                 h_{t_0} : [ 2.86e+05  2.66e+05  2.39e+05  2.35e+05  2.29e+05    [J/kg]        Free Stream Stagnation Enthalpy\n",
      "                             2.86e+05  2.66e+05  2.39e+05  2.35e+05  2.29e+05  ]\n",
      "                 h_{t_3} : [ 7.73e+05  8.48e+05  7.61e+05  5.68e+05  5.72e+05    [J/kg]        Stagnation Enthalpy at the HPC Exit (3)\n",
      "                             7.73e+05  8.48e+05  7.61e+05  5.68e+05  5.72e+05  ]\n",
      "                 h_{t_7} : [ 3.23e+05  3.09e+05  2.77e+05  2.6e+05   2.55e+05    [J/kg]        Stagnation Enthalpy at the Fan Nozzle Exit (7)\n",
      "                             3.23e+05  3.09e+05  2.77e+05  2.6e+05   2.55e+05  ]\n",
      "             h_{t_{1.8}} : [ 2.86e+05  2.66e+05  2.39e+05  2.35e+05  2.29e+05    [J/kg]        Stagnation Enthalpy at the Diffuser Exit (1.8)\n",
      "                             2.86e+05  2.66e+05  2.39e+05  2.35e+05  2.29e+05  ]\n",
      "             h_{t_{2.1}} : [ 3.23e+05  3.09e+05  2.77e+05  2.6e+05   2.55e+05    [J/kg]        Stagnation Enthalpy at the Fan Exit (2.1)\n",
      "                             3.23e+05  3.09e+05  2.77e+05  2.6e+05   2.55e+05  ]\n",
      "             h_{t_{2.5}} : [ 3.67e+05  4.1e+05   3.6e+05   2.6e+05   2.65e+05    [J/kg]        Stagnation Enthalpy at the LPC Exit (2.5)\n",
      "                             3.67e+05  4.1e+05   3.6e+05   2.6e+05   2.65e+05  ]\n",
      "              hold_{2.5} : [ 1.06      1.06      1.06      1.06      1.06                      1+(gamma-1)/2 * M_2.5**2\n",
      "                             1.06      1.06      1.06      1.06      1.06      ]\n",
      "                hold_{2} : [ 1.07      1.07      1.07      1.07      1.07                      1+(gamma-1)/2 * M_2**2\n",
      "                             1.07      1.07      1.07      1.07      1.07      ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/FanMapPerformance.1\n",
      "                   N_{f} : [ 0.948     1.04      1.03      0.882     0.901                     Fan Speed\n",
      "                             0.948     1.04      1.03      0.882     0.901     ]\n",
      "                   m_{f} : [ 406       481       494       449       449         [kg/s]        Fan Corrected Mass Flow\n",
      "                             406       481       494       449       449       ]\n",
      "              m_{tild_f} : [ 0.841     0.998     1.02      0.931     0.931                     Fan Normalized Mass Flow\n",
      "                             0.841     0.998     1.02      0.931     0.931     ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/HPCMapPerformance.1\n",
      "                   N_{2} : [ 1.02      1.01      1.02      1.04      1.04                      HPC Speed\n",
      "                             1.02      1.01      1.02      1.04      1.04      ]\n",
      "                  m_{hc} : [ 14.1      14.1      14.1      14.1      14.1        [kg/s]        HPC Corrected Mass Flow\n",
      "                             14.1      14.1      14.1      14.1      14.1      ]\n",
      "           m_{tild_{hc}} : [ 1.13      1.13      1.13      1.13      1.13                      HPC Normalized Mass Flow\n",
      "                             1.13      1.13      1.13      1.13      1.13      ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/LPCMapPerformance.1\n",
      "                   N_{1} : [ 0.948     1.04      1.03      0.882     0.901                     LPC Speed\n",
      "                             0.948     1.04      1.03      0.882     0.901     ]\n",
      "                  m_{lc} : [ 27.2      41.3      42.6      21.1      22.8        [kg/s]        LPC Corrected Mass Flow\n",
      "                             27.2      41.3      42.6      21.1      22.8      ]\n",
      "             m_{tild_lc} : [ 0.751     1.14      1.17      0.582     0.63                      LPC Normalized Mass Flow\n",
      "                             0.751     1.14      1.17      0.582     0.63      ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/SizingPerformance.1\n",
      "                     M_2 : [ 0.651     0.772     0.793     0.72      0.72                      Fan Face/LPC Face Axial Mach Number\n",
      "                             0.651     0.772     0.793     0.72      0.72      ]\n",
      "                     M_5 : [ 0.35      0.43      0.341     0.302     0.324                     Station 5 Mach Number\n",
      "                             0.35      0.43      0.341     0.302     0.324     ]\n",
      "                     M_7 : [ 0.636     0.753     0.787     0.777     0.764                     Station 7 Mach Number\n",
      "                             0.636     0.753     0.787     0.777     0.764     ]\n",
      "                 M_{2.5} : [ 0.6       0.6       0.6       0.6       0.6                       HPC Face Axial Mach Number\n",
      "                             0.6       0.6       0.6       0.6       0.6       ]\n",
      "                 P_{2.5} : [ 139       162       85.3      29.7      29.8        [kPa]         Static Air Pressure at HPC Face\n",
      "                             139       162       85.3      29.7      29.8      ]\n",
      "                   P_{2} : [ 62.3      40.7      22.9      21.4      18.8        [kPa]         Air Static Pressure at Fan Face\n",
      "                             62.3      40.7      22.9      21.4      18.8      ]\n",
      "                   P_{5} : [ 73.1      63.5      46.8      21        18.7        [kPa]         Core Exhaust Static Pressure (5)\n",
      "                             73        63.6      46.8      21        18.7      ]\n",
      "                   P_{7} : [ 76.7      50.3      27.7      23.4      20.9        [kPa]         Fan Exhaust Static Pressure (7)\n",
      "                             76.7      50.3      27.7      23.4      20.9      ]\n",
      "                 T_{2.5} : [ 342       382       336       243       247         [K]           Static Air Temperature at HPC Face\n",
      "                             342       382       336       243       247       ]\n",
      "                   T_{2} : [ 266       248       223       218       213         [K]           Air Static Temperature at Fan Face\n",
      "                             266       248       223       218       213       ]\n",
      "                   T_{5} : [ 666       623       672       632       590         [K]           Static Temperature at the Turbine Nozzle Exit (5)\n",
      "                             665       624       672       632       590       ]\n",
      "                   T_{7} : [ 287       269       240       227       223         [K]           Static Temperature at the Fan Nozzle Exit (7)\n",
      "                             287       269       240       227       223       ]\n",
      "                  \\rho_5 : [ 0.382     0.355     0.242     0.116     0.111       [kg/m³]       Air Static Density at Core Exhaust Exit (5)\n",
      "                             0.382     0.355     0.242     0.116     0.111     ]\n",
      "                  \\rho_7 : [ 0.93      0.652     0.402     0.358     0.327       [kg/m³]       Air Static Density at Fam Exhaust Exit (7)\n",
      "                             0.93      0.652     0.402     0.358     0.327     ]\n",
      "              \\rho_{2.5} : [ 1.41      1.48      0.884     0.426     0.42        [kg/m³]       Static Air Density at HPC Face\n",
      "                             1.41      1.48      0.884     0.426     0.42      ]\n",
      "                \\rho_{2} : [ 0.816     0.573     0.359     0.341     0.307       [kg/m³]       Air Static Density at Fan Face\n",
      "                             0.816     0.573     0.359     0.341     0.307     ]\n",
      "                   a_{5} : [ 515       498       517       502       485         [m/s]         Speed of Sound at Station 5\n",
      "                             515       498       517       502       485       ]\n",
      "                   a_{7} : [ 340       328       310       302       299         [m/s]         Speed of Sound at Station 7\n",
      "                             340       328       310       302       299       ]\n",
      "                     dum : [ 781       781       781       781       781         [J/K/kg]\n",
      "                             781       781       781       781       781       ]\n",
      "                    dum2 : [ 1         1         1         1         1           [m/s]\n",
      "                             1         1         1         1         1         ]\n",
      "                 h_{2.5} : [ 3.76e+05  4.2e+05   3.69e+05  2.67e+05  2.71e+05    [J/kg]        Static Enthalpy at the LPC Exit (2.5)\n",
      "                             3.76e+05  4.2e+05   3.69e+05  2.67e+05  2.71e+05  ]\n",
      "                   h_{2} : [ 2.68e+05  2.5e+05   2.24e+05  2.2e+05   2.15e+05    [J/kg]        Static Enthalpy at the Fan Inlet (2)\n",
      "                             2.68e+05  2.5e+05   2.24e+05  2.2e+05   2.15e+05  ]\n",
      "               m_{total} : [ 342       304       229       204       192         [kg/s]        Total Engine Mass Flux\n",
      "                             342       304       229       204       192       ]\n",
      "                 u_{2.5} : [ 223       236       221       188       189         [m/s]         Air Speed at HPC Face\n",
      "                             223       236       221       188       189       ]\n",
      "                   u_{2} : [ 204       234       228       205       202         [m/s]         Air Speed at Fan Face\n",
      "                             204       234       228       205       202       ]\n",
      "                   u_{5} : [ 180       214       176       152       157         [m/s]         Station 5 Exhaust Velocity\n",
      "                             180       214       176       152       157       ]\n",
      "                   u_{7} : [ 216       247       244       235       229         [m/s]         Station 7 Exhaust Velocity\n",
      "                             216       247       244       235       229       ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/SizingPerformance.1/Relax.1\n",
      "                     dum : [ 1         1         1         1         1\n",
      "                             1         1         1         1         1         ]\n",
      "                    dum2 : [ 1         1         1         1         1\n",
      "                             1         1         1         1         1         ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/ThrustPerformance.1\n",
      "                       F : [ 4.45e+04  4.32e+04  2.6e+04   1.28e+04  1.19e+04    [N]           Total Thrust\n",
      "                             4.45e+04  4.32e+04  2.6e+04   1.28e+04  1.19e+04  ]\n",
      "                   F_{6} : [ 4.17e+03  8.7e+03   6.59e+03  196       358         [N]           Core Thrust\n",
      "                             4.17e+03  8.7e+03   6.59e+03  196       358       ]\n",
      "                   F_{8} : [ 4.03e+04  3.45e+04  1.94e+04  1.26e+04  1.16e+04    [N]           Fan Thrust\n",
      "                             4.03e+04  3.45e+04  1.94e+04  1.26e+04  1.16e+04  ]\n",
      "                  F_{sp} : [ 0.401     0.498     0.524     0.313     0.332                     Specific Net Thrust\n",
      "                             0.401     0.498     0.524     0.313     0.332     ]\n",
      "                  I_{sp} : [ 6.98e+03  6.53e+03  6.5e+03   7.76e+03  7.86e+03    [s]           Specific Impulse\n",
      "                             6.98e+03  6.53e+03  6.5e+03   7.76e+03  7.86e+03  ]\n",
      "                   P_{6} : [ 62.4      36.5      20.1      20.1      17.7        [kPa]         Core Exhaust Static Pressure\n",
      "                             62.4      36.5      20.1      20.1      17.7      ]\n",
      "                   P_{8} : [ 62.4      36.5      20.1      20.1      17.7        [kPa]         Fan Exhaust Static Pressure\n",
      "                             62.4      36.5      20.1      20.1      17.7      ]\n",
      "                 P_{t_6} : [ 95.6      103       83.2      23.8      22          [kPa]         Core Exhaust Stagnation Pressure\n",
      "                             95.6      103       83.2      23.8      22        ]\n",
      "                 P_{t_8} : [ 115       81.2      45.3      37        33.1        [kPa]         Fan Exhaust Stagnation Pressure\n",
      "                             115       81.2      45.3      37        33.1      ]\n",
      "                    TSFC : [ 0.516     0.551     0.554     0.464     0.458       [1/hr]        Thrust Specific Fuel Consumption\n",
      "                             0.516     0.551     0.554     0.464     0.458     ]\n",
      "                   T_{6} : [ 637       534       531       625       581         [K]           Core Exhaust Static Temperature (6)\n",
      "                             637       534       531       625       581       ]\n",
      "                   T_{8} : [ 271       245       219       218       213         [K]           Fan Exhaust Sttic Temperature (8)\n",
      "                             271       245       219       218       213       ]\n",
      "                 T_{t_6} : [ 717       714       789       655       617         [K]           Core Exhaust Stagnation Temperature (6)\n",
      "                             717       714       789       655       617       ]\n",
      "                 T_{t_8} : [ 322       308       276       259       254         [K]           Fan Exhaust Stagnation Temperature (8)\n",
      "                             322       308       276       259       254       ]\n",
      "                  \\alpha : [ 14.8      10.7      11.6      24.3      21.7                      By Pass Ratio\n",
      "                             14.8      10.7      11.6      24.3      21.7      ]\n",
      "             \\alpha_{+1} : [ 15.8      11.7      12.6      25.3      22.7                      1 plus BPR\n",
      "                             15.8      11.7      12.6      25.3      22.7      ]\n",
      "                     h_6 : [ 6.55e+05  5.5e+05   5.47e+05  6.43e+05  5.97e+05    [J/kg]        Core Exhasut Static Enthalpy\n",
      "                             6.55e+05  5.5e+05   5.47e+05  6.43e+05  5.97e+05  ]\n",
      "                   h_{8} : [ 2.72e+05  2.46e+05  2.2e+05   2.19e+05  2.14e+05    [J/kg]        Fan Exhasut Static Enthalpy\n",
      "                             2.72e+05  2.46e+05  2.2e+05   2.19e+05  2.14e+05  ]\n",
      "                 h_{t_6} : [ 7.38e+05  7.35e+05  8.12e+05  6.74e+05  6.35e+05    [J/kg]        Core Exhaust Stagnation Enthalpy\n",
      "                             7.38e+05  7.35e+05  8.12e+05  6.74e+05  6.35e+05  ]\n",
      "                 h_{t_8} : [ 3.24e+05  3.1e+05   2.77e+05  2.61e+05  2.56e+05    [J/kg]        Fan Exhaust Stagnation Enthalpy\n",
      "                             3.24e+05  3.1e+05   2.77e+05  2.61e+05  2.56e+05  ]\n",
      "                    hold : [ 15.8      11.7      12.6      25.3      22.7                      unecessary hold var\n",
      "                             15.8      11.7      12.6      25.3      22.7      ]\n",
      "                m_{core} : [ 21.7      24        13.5      5.51      5.48        [kg/s]        Core Mass Flow\n",
      "                             21.7      24        13.5      5.51      5.48      ]\n",
      "                 m_{fan} : [ 320       257       157       134       119         [kg/s]        Fan Mass Flow\n",
      "                             320       257       157       134       119       ]\n",
      "                   u_{6} : [ 407       608       729       246       274         [m/s]         Core Exhaust Velocity\n",
      "                             407       608       729       246       274       ]\n",
      "                   u_{8} : [ 322       355       338       288       290         [m/s]         Fan Exhaust Velocity\n",
      "                             322       355       338       288       290       ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/TurbinePerformance.1\n",
      "                 P_{t_5} : [ 95.6      103       83.2      23.8      22          [kPa]         Stagnation Pressure at the Turbine Nozzle Exit (5)\n",
      "                             95.6      103       83.2      23.8      22        ]\n",
      "             P_{t_{4.5}} : [ 684       694       431       196       183         [kPa]         Stagnation Pressure at the HPT Exit (4.5)\n",
      "                             684       694       431       196       183       ]\n",
      "             P_{t_{4.9}} : [ 96.1      104       83.7      23.9      22.1        [kPa]         Stagnation Pressure at the HPTExit (49)\n",
      "                             96.1      104       83.7      23.9      22.1      ]\n",
      "                 T_{t_5} : [ 717       714       789       655       617         [K]           Stagnation Temperature at the Turbine Nozzle Exit (5)\n",
      "                             717       714       789       655       617       ]\n",
      "             T_{t_{4.5}} : [ 1.25e+03  1.23e+03  1.26e+03  1.19e+03  1.12e+03    [K]           Stagnation Temperature at the HPT Exit (4.5)\n",
      "                             1.25e+03  1.23e+03  1.26e+03  1.19e+03  1.12e+03  ]\n",
      "             T_{t_{4.9}} : [ 717       714       789       655       617         [K]           Stagnation Temperature at the HPT Exit (49)\n",
      "                             717       714       789       655       617       ]\n",
      "               \\pi_{HPT} : [ 0.431     0.395     0.437     0.508     0.488                     HPT Pressure Ratio\n",
      "                             0.431     0.395     0.437     0.508     0.488     ]\n",
      "               \\pi_{LPT} : [ 0.14      0.149     0.194     0.122     0.121                     LPT Pressure Ratio\n",
      "                             0.14      0.149     0.194     0.122     0.121     ]\n",
      "                 h_{t_5} : [ 8.61e+05  8.57e+05  9.48e+05  7.86e+05  7.41e+05    [J/kg]        Stagnation Enthalpy at the Turbine Nozzle Exit (5)\n",
      "                             8.61e+05  8.57e+05  9.48e+05  7.86e+05  7.41e+05  ]\n",
      "             h_{t_{4.5}} : [ 1.55e+06  1.52e+06  1.56e+06  1.47e+06  1.39e+06    [J/kg]        Stagnation Enthalpy at the HPT Exit (4.5)\n",
      "                             1.55e+06  1.52e+06  1.56e+06  1.47e+06  1.39e+06  ]\n",
      "             h_{t_{4.9}} : [ 8.61e+05  8.57e+05  9.48e+05  7.86e+05  7.41e+05    [J/kg]        Stagnation Enthalpy at the HPT Exit (49)\n",
      "                             8.61e+05  8.57e+05  9.48e+05  7.86e+05  7.41e+05  ]\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/FanMap.1\n",
      "       \\bar{m}_{fan_{D}} : 482.2                                                 [kg/s]        Fan On-Design Corrected Mass Flow\n",
      "               \\pi_{f_D} : 1.605                                                               On-Design Pressure Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/FanMap.1/Relax.1\n",
      "               \\pi_{f_D} : 1                                                                   On-Design Pressure Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/HPCMap.1\n",
      "              \\pi_{hc_D} : 8.697                                                               HPC On-Design Pressure Ratio\n",
      "                m_{hc_D} : 12.41                                                 [kg/s]        On Design HPC Corrected Mass Flow\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/LPCMap.1\n",
      "              \\pi_{lc_D} : 2.11                                                                LPC On-Design Pressure Ratio\n",
      "                m_{lc_D} : 36.28                                                 [kg/s]        On Design LPC Corrected Mass Flow\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Relax.1\n",
      "           HTR_{f_{SUB}} : 1                                                                   1 - HTRf^2\n",
      "         HTR_{lpc_{SUB}} : 1                                                                   1 - HTRlpc^2\n",
      "       T_{t_{4.1_{max}}} : 1                                                                   Max turbine inlet temperature\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Sizing.1\n",
      "                 A_{2.5} : 0.06885                                               [m²]          HPC Area\n",
      "                   A_{2} : 1.918                                                 [m²]          Fan Area\n",
      "                   A_{5} : 0.3099                                                [m²]          Core Exhaust Nozzle Area\n",
      "                   A_{7} : 1.593                                                 [m²]          Fan Exhaust Nozzle Area\n",
      "                   G_{f} : 1                                                                   Gear Ratio Between Fan and LPC\n",
      "             \\alpha_{OD} : 8.923                                                               By Pass Ratio\n",
      "               m_{coreD} : 24.6                                                  [kg/s]        Estimated on Design Mass Flow\n",
      "                 m_{htD} : 3.172                                                 [kg/s]        Design HPT Corrected Mass Flow (see B.225)\n",
      "                 m_{ltD} : 6.53                                                  [kg/s]        Design LPT Corrected Mass Flow (see B.226)\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Sizing.1/Relax.1\n",
      "                   G_{f} : 1                                                                   Gear Ratio Between Fan and LPC\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Thrust.1\n",
      "              C_{p_{fex} : 1005                                                  [J/K/kg]      Cp Value for Air at 300K\n",
      "              C_{p_{tex} : 1029                                                  [J/K/kg]      Cp Value for Combustion Products at Core Exhaust\n",
      "            \\alpha_{max} : 1e+30                                                               By Pass Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Thrust.1/Relax.1\n",
      "              C_{p_{fex} : 1                                                                   Cp Value for Air at 300K\n",
      "              C_{p_{tex} : 1                                                                   Cp Value for Combustion Products at Core Exhaust\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Turbine.1\n",
      "              C_{p_{t1}} : 1236                                                  [J/K/kg]      Cp Value for Combustion Products in HP Turbine\n",
      "              C_{p_{t2}} : 1200                                                  [J/K/kg]      Cp Value for Combustion Products in LP Turbine\n",
      "          \\eta_{HPshaft} : 0.978                                                               Power Transmission Efficiency of High Pressure Shaft, Smears in Losses for Electrical Power\n",
      "          \\eta_{LPshaft} : 0.99                                                                Power Transmission Efficiency of Low Pressure Shaft, Smeras in Losses for Electrical Power\n",
      "                \\pi_{tn} : 0.995                                                               Turbine Nozzle Pressure Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Engine.1/Turbine.1/Relax.1\n",
      "              C_{p_{t1}} : 1                                                                   Cp Value for Combustion Products in HP Turbine\n",
      "              C_{p_{t2}} : 1                                                                   Cp Value for Combustion Products in LP Turbine\n",
      "          \\eta_{HPshaft} : 1                                                                   Power Transmission Efficiency of High Pressure Shaft, Smears in Losses for Electrical Power\n",
      "          \\eta_{LPshaft} : 1                                                                   Power Transmission Efficiency of Low Pressure Shaft, Smeras in Losses for Electrical Power\n",
      "                \\pi_{tn} : 1                                                                   Turbine Nozzle Pressure Ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Fuselage.1\n",
      "                  A_{0h} : 0.01067                                               [m²]          Horizontal bending area constant A0h\n",
      "           A_{1h_{Land}} : 0.001781                                              [m]           Horizontal bending area constant A1h (landing case)\n",
      "            A_{1h_{MLF}} : 0.002003                                              [m]           Horizontal bending area constant A1h (max aero load case)\n",
      "           A_{2h_{Land}} : 0.0001477                                                           Horizontal bending area constant A2h (landing case)\n",
      "            A_{2h_{MLF}} : 7.562e-05                                                           Horizontal bending area constant A2h (max aero load case)\n",
      "                  A_{db} : 0.003387                                              [m²]          Web cross sectional area\n",
      "               A_{floor} : 0.01032                                               [m²]          Floor beam x-sectional area\n",
      "                A_{fuse} : 16.03                                                 [m²]          Fuselage x-sectional area\n",
      "       A_{hbendb_{Land}} : 0.01631                                               [m²]          Horizontal bending area at rear wingbox (landing case)\n",
      "        A_{hbendb_{MLF}} : 0.01517                                               [m²]          Horizontal bending area at rear wingbox (max aero load case)\n",
      "       A_{hbendf_{Land}} : 0.006209                                              [m²]          Horizontal bending area at front wingbox (landing case)\n",
      "        A_{hbendf_{MLF}} : 0.006886                                              [m²]          Horizontal bending area at front wingbox (max aero load case)\n",
      "                A_{skin} : 0.01418                                               [m²]          Skin cross sectional area\n",
      "           A_{vbend_{b}} : 0.0009953                                             [m²]          Vertical bending material area at rear wingbox\n",
      "                  B_{0v} : 0.006134                                              [m²]          Vertical bending area constant B0\n",
      "                  B_{1v} : 0.0006885                                             [m]           Vertical bending area constant B1\n",
      "                C_{fuse} : 1                                                                   Fuselage Weight Margin and Sensitivity\n",
      "           I_{h_{shell}} : 0.03799                                               [m⁴]          Shell horizontal bending inertia\n",
      "           I_{v_{shell}} : 0.0418                                                [m⁴]          Shell vertical bending inertia\n",
      "               M_{floor} : 1.043e+05                                             [N·m]         Max bending moment in floor beams\n",
      "               M_{fuseD} : 0.72                                                                Fuselage Drag Reference Mach\n",
      "                N_{land} : 6                                                                   Emergency landing load factor\n",
      "                N_{lift} : 3                                                                   Wing maximum load factor\n",
      "               P_{floor} : 1.136e+06                                             [N]           Distributed floor load\n",
      "                R_{fuse} : 1.681                                                 [m]           Fuselage radius\n",
      "                     SPR : 8                                                                   Number of seats per row\n",
      "                S_{bulk} : 24                                                    [m²]          Bulkhead surface area\n",
      "               S_{floor} : 3.551e+05                                             [N]           Maximum shear in floor beams\n",
      "                S_{nose} : 24                                                    [m²]          Nose surface area\n",
      "                V_{bulk} : 0.02253                                               [m³]          Bulkhead skin volume\n",
      "               V_{cabin} : 405.2                                                 [m³]          Cabin volume\n",
      "                V_{cone} : 0.02874                                               [m³]          Cone skin volume\n",
      "                 V_{cyl} : 0.2584                                                [m³]          Cylinder skin volume\n",
      "                  V_{db} : 0.06172                                               [m³]          Web volume\n",
      "               V_{floor} : 0.05391                                               [m³]          Floor volume\n",
      "           V_{hbend_{b}} : 0.042                                                 [m³]          Horizontal bending material volume b\n",
      "           V_{hbend_{c}} : 0.03255                                               [m³]          Horizontal bending material volume c\n",
      "           V_{hbend_{f}} : 0.0146                                                [m³]          Horizontal bending material volume f\n",
      "               V_{hbend} : 0.08915                                               [m³]          Horizontal bending material volume\n",
      "                V_{nose} : 0.02253                                               [m³]          Nose skin volume\n",
      "           V_{vbend_{b}} : 0.0007522                                             [m³]          Vertical bending material volume b\n",
      "           V_{vbend_{c}} : 0.001439                                              [m³]          Vertical bending material volume c\n",
      "               V_{vbend} : 0.002191                                              [m³]          Vertical bending material volume\n",
      "             W''_{floor} : 60                                                    [N/m²]        Floor weight/area density\n",
      "             W''_{insul} : 22                                                    [N/m²]        Weight/area density of insulation material\n",
      "               W'_{seat} : 1                                                     [N]           Weight per seat\n",
      "             W'_{window} : 435                                                   [N/m]         Weight/length density of windows\n",
      "                 W_{apu} : 1355                                                  [lbf]         APU weight\n",
      "   W_{avg. pass_{total}} : 215                                                   [lbf]         Average passenger weight including payload\n",
      "           W_{avg. pass} : 180                                                   [lbf]         Average passenger weight\n",
      "               W_{cargo} : 0.02248                                               [lbf]         Cargo weight\n",
      "            W_{carry on} : 15                                                    [lbf]         Ave. carry-on weight\n",
      "             W_{checked} : 40                                                    [lbf]         Ave. checked bag weight\n",
      "                W_{cone} : 273.8                                                 [lbf]         Cone weight\n",
      "                  W_{db} : 367.5                                                 [lbf]         Web weight\n",
      "                 W_{fix} : 3000                                                  [lbf]         Fixed weights (pilots, cockpit seats, navcom)\n",
      "               W_{floor} : 1841                                                  [lbf]         Floor weight\n",
      "                W_{fuse} : 3.065e+04                                             [lbf]         Fuselage weight\n",
      "               W_{hbend} : 530.8                                                 [lbf]         Horizontal bending material weight\n",
      "               W_{insul} : 821.7                                                 [lbf]         Insulation material weight\n",
      "                W_{padd} : 1.355e+04                                             [lbf]         Misc weights (galley, toilets, doors etc.)\n",
      "       W_{payload_{max}} : 3.87e+04                                              [lbf]         Maximum payload weight\n",
      "                W_{seat} : 3870                                                  [lbf]         Seating weight\n",
      "               W_{shell} : 3621                                                  [lbf]         Shell weight\n",
      "                W_{skin} : 1807                                                  [lbf]         Skin weight\n",
      "                W_{tail} : 757.8                                                 [lbf]         Total tail weight\n",
      "               W_{vbend} : 13.05                                                 [lbf]         Vertical bending material weight\n",
      "              W_{window} : 1782                                                  [lbf]         Window weight\n",
      "         \\Delta P_{over} : 8.382                                                 [psi]         Cabin overpressure\n",
      "         \\Delta R_{fuse} : 0.4129                                                [m]           Fuselage extension height\n",
      "          \\lambda_{cone} : 0.3                                                                 Tailcone radius taper ratio\n",
      "             \\rho_{bend} : 2700                                                  [kg/m³]       Stringer density\n",
      "            \\rho_{cargo} : 150                                                   [kg/m³]       Cargo density\n",
      "             \\rho_{cone} : 2700                                                  [kg/m³]       Cone material density\n",
      "            \\rho_{floor} : 2700                                                  [kg/m³]       Floor material density\n",
      "             \\rho_{lugg} : 100                                                   [kg/m³]       Luggage density\n",
      "             \\rho_{skin} : 2700                                                  [kg/m³]       Skin density\n",
      "                \\sigma_x : 3.831e+07                                             [N/m²]        Axial stress in skin\n",
      "            \\sigma_{M_h} : 1.686e+08                                             [N/m²]        Horizontal bending material stress\n",
      "            \\sigma_{M_v} : 1.686e+08                                             [N/m²]        Vertical bending material stress\n",
      "         \\sigma_{\\theta} : 1.034e+08                                             [N/m²]        Skin hoop stress\n",
      "           \\sigma_{bend} : 2.069e+08                                             [N/m²]        Bending material stress\n",
      "          \\sigma_{floor} : 2.069e+08                                             [N/m²]        Max allowable floor stress\n",
      "           \\sigma_{skin} : 1.034e+08                                             [N/m²]        Max allowable skin stress\n",
      "             \\tau_{cone} : 1.034e+08                                             [N/m²]        Shear stress in cone\n",
      "            \\tau_{floor} : 2.069e+08                                             [N/m²]        Max allowable shear web stress\n",
      "             \\theta_{db} : 0.5534                                                              DB fuselage joining angle\n",
      "                     c_0 : 5.783                                                 [m]           Root chord of the wing\n",
      "                 f_{apu} : 0.035                                                               APU weight as fraction of payload weight\n",
      "                f_{fadd} : 0.2                                                                 Fractional added weight of local reinforcements\n",
      "               f_{frame} : 0.25                                                                Fractional frame weight\n",
      "              f_{lugg,1} : 0.4                                                                 Proportion of passengers with one suitcase\n",
      "              f_{lugg,2} : 0.1                                                                 Proportion of passengers with two suitcases\n",
      "                f_{padd} : 0.35                                                                Other misc weight as fraction of payload weight\n",
      "                f_{seat} : 0.1                                                                 Fractional seat weight\n",
      "              f_{string} : 0.35                                                                Fractional stringer weight\n",
      "                       g : 9.81                                                  [m/s²]        Acceleration due to gravity\n",
      "                  h_{db} : 1.423                                                 [m]           Web half-height\n",
      "               h_{floor} : 0.13                                                  [m]           Floor beam height\n",
      "                h_{fuse} : 1.887                                                 [m]           Fuselage height\n",
      "                l_{cone} : 5.602                                                 [m]           Cone length\n",
      "               l_{floor} : 21.59                                                 [m]           Floor length\n",
      "                l_{fuse} : 32.67                                                 [m]           Fuselage length\n",
      "                l_{nose} : 8.839                                                 [m]           Nose length\n",
      "               l_{shell} : 18.22                                                 [m]           Shell length\n",
      "                n_{rows} : 22.5                                                                Number of rows\n",
      "                n_{seat} : 180                                                                 Number of seats\n",
      "                     p_s : 81                                                    [cm]          Seat pitch\n",
      "        p_{\\lambda_{vt}} : 1.6                                                                 1 + 2*Tail taper ratio\n",
      "                     r_E : 1                                                                   Ratio of stringer/skin moduli\n",
      "                 r_{M_h} : 0.4                                                                 Horizontal inertial relief factor\n",
      "                 r_{M_v} : 0.7                                                                 Vertical inertial relief factor\n",
      "                 r_{w/c} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "                  t_{db} : 0.001039                                              [m]           Web thickness\n",
      "               t_{shell} : 0.001267                                              [m]           Shell thickness\n",
      "                t_{skin} : 0.0009388                                             [m]           Skin thickness\n",
      "               w_{aisle} : 0.51                                                  [m]           Aisle width\n",
      "                  w_{db} : 0.93                                                  [m]           DB added half-width\n",
      "               w_{floor} : 2.611                                                 [m]           Floor half-width\n",
      "                w_{fuse} : 2.611                                                 [m]           Fuselage half-width\n",
      "                w_{seat} : 0.5                                                   [m]           Seat width\n",
      "                 w_{sys} : 0.1                                                   [m]           Width between cabin and skin for systems\n",
      "                     x_b : 19.51                                                 [m]           x-location of back of wingbox\n",
      "                     x_f : 22.4                                                  [m]           x-location of front of wingbox\n",
      "        x_{hbend_{Land}} : 80.2                                                  [ft]          Horizontal zero bending location (landing case)\n",
      "         x_{hbend_{MLF}} : 81.18                                                 [ft]          Horizontal zero bending location (maximum aero load case)\n",
      "              x_{shell1} : 8.839                                                 [m]           Start of cylinder section\n",
      "              x_{shell2} : 27.06                                                 [m]           End of cylinder section\n",
      "                x_{tail} : 29.87                                                 [m]           x-location of tail\n",
      "               x_{vbend} : 68.75                                                 [ft]          Vertical zero bending location\n",
      "                x_{wing} : 20.96                                                 [m]           x-location of wing c/4\n",
      "                W_{lugg} : [ 5.13e+03  5.13e+03 ]                                [lbf]         Passenger luggage weight\n",
      "                W_{pass} : [ 3.28e+04  3.28e+04 ]                                [lbf]         Passenger weight\n",
      "             W_{payload} : [ 3.87e+04  3.87e+04 ]                                [lbf]         Payload weight\n",
      "                n_{pass} : [ 180       180      ]                                              Number of passengers\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Fuselage.1/Relax.1\n",
      "                C_{fuse} : 1                                                                   Fuselage Weight Margin and Sensitivity\n",
      "                N_{land} : 1                                                                   Emergency landing load factor\n",
      "                     SPR : 1                                                                   Number of seats per row\n",
      "             W''_{floor} : 1                                                                   Floor weight/area density\n",
      "             W''_{insul} : 1                                                                   Weight/area density of insulation material\n",
      "               W'_{seat} : 1                                                                   Weight per seat\n",
      "             W'_{window} : 1                                                                   Weight/length density of windows\n",
      "   W_{avg. pass_{total}} : 1                                                                   Average passenger weight including payload\n",
      "           W_{avg. pass} : 1                                                                   Average passenger weight\n",
      "               W_{cargo} : 1                                                                   Cargo weight\n",
      "            W_{carry on} : 1                                                                   Ave. carry-on weight\n",
      "             W_{checked} : 1                                                                   Ave. checked bag weight\n",
      "                 W_{fix} : 1                                                                   Fixed weights (pilots, cockpit seats, navcom)\n",
      "         \\Delta P_{over} : 1                                                                   Cabin overpressure\n",
      "          \\lambda_{cone} : 1                                                                   Tailcone radius taper ratio\n",
      "             \\rho_{bend} : 1                                                                   Stringer density\n",
      "            \\rho_{cargo} : 1                                                                   Cargo density\n",
      "             \\rho_{cone} : 1                                                                   Cone material density\n",
      "            \\rho_{floor} : 1                                                                   Floor material density\n",
      "             \\rho_{lugg} : 1                                                                   Luggage density\n",
      "             \\rho_{skin} : 1                                                                   Skin density\n",
      "           \\sigma_{bend} : 1                                                                   Bending material stress\n",
      "          \\sigma_{floor} : 1                                                                   Max allowable floor stress\n",
      "           \\sigma_{skin} : 1                                                                   Max allowable skin stress\n",
      "            \\tau_{floor} : 1                                                                   Max allowable shear web stress\n",
      "                 f_{apu} : 1                                                                   APU weight as fraction of payload weight\n",
      "                f_{fadd} : 1                                                                   Fractional added weight of local reinforcements\n",
      "               f_{frame} : 1                                                                   Fractional frame weight\n",
      "              f_{lugg,1} : 1                                                                   Proportion of passengers with one suitcase\n",
      "              f_{lugg,2} : 1                                                                   Proportion of passengers with two suitcases\n",
      "                f_{padd} : 1                                                                   Other misc weight as fraction of payload weight\n",
      "                f_{seat} : 1                                                                   Fractional seat weight\n",
      "              f_{string} : 1                                                                   Fractional stringer weight\n",
      "                       g : 1                                                                   Acceleration due to gravity\n",
      "               h_{floor} : 1                                                                   Floor beam height\n",
      "                l_{nose} : 1                                                                   Nose length\n",
      "                     p_s : 1                                                                   Seat pitch\n",
      "        p_{\\lambda_{vt}} : 1                                                                   1 + 2*Tail taper ratio\n",
      "                     r_E : 1                                                                   Ratio of stringer/skin moduli\n",
      "                 r_{M_h} : 1                                                                   Horizontal inertial relief factor\n",
      "                 r_{M_v} : 1                                                                   Vertical inertial relief factor\n",
      "                 r_{w/c} : 1                                                                   Wingbox width-to-chord ratio\n",
      "               w_{aisle} : 1                                                                   Aisle width\n",
      "                  w_{db} : 1                                                                   DB added half-width\n",
      "                w_{seat} : 1                                                                   Seat width\n",
      "                 w_{sys} : 1                                                                   Width between cabin and skin for systems\n",
      "                n_{pass} : [ 1         1        ]                                              Number of passengers\n",
      "\n",
      "                         | Mission.1/Aircraft.1/HorizontalTail.1\n",
      "                  C_{ht} : 1                                                                   HT Weight Margin and Sensitivity Factor\n",
      "                  W_{ht} : 668.9                                                 [N]           HT System Weight\n",
      "    \\cos(\\Lambda_{ht})^3 : 0.9711                                                              Cosine of tail sweep cubed\n",
      "              c_{d_{fh}} : 0.006                                                               VT friction drag coefficient\n",
      "              c_{d_{ph}} : 0.0035                                                              VT pressure drag coefficient\n",
      "                  f_{ht} : 0.3                                                                 Rudder etc. fractional weight\n",
      "\n",
      "                         | Mission.1/Aircraft.1/HorizontalTail.1/HorizontalTailNoStruct.1\n",
      "                 AR_{ht} : 5.297                                                               Horizontal tail aspect ratio\n",
      "          C_{L_{ht,fCG}} : 0.85                                                                HT CL During Max Forward CG\n",
      "          C_{L_{ht,max}} : 2                                                                   Max lift coefficient\n",
      "            L_{ht_{max}} : 7.758e+05                                             [N]           Maximum load\n",
      "                  S_{ht} : 30.58                                                 [m²]          Horizontal tail area\n",
      "                  V_{ht} : 0.6538                                                              Horizontal Tail Volume Coefficient\n",
      "    \\Delta x_{lead_{ht}} : 10.45                                                 [m]           Distance from CG to horizontal tail leading edge\n",
      "   \\Delta x_{trail_{ht}} : 14.15                                                 [m]           Distance from CG to horizontal tail trailing edge\n",
      "         \\alpha_{ht,max} : 2.5                                                                 Max angle of attack, htail\n",
      "            \\bar{c}_{ht} : 2.635                                                 [m]           Mean aerodynamic chord (ht)\n",
      "               \\eta_{ht} : 1                                                                   Tail efficiency\n",
      "            \\lambda_{ht} : 0.3                                                                 Horizontal tail taper ratio\n",
      "      \\tan(\\Lambda_{ht}) : 0.1405                                                              tangent of horizontal tail sweep\n",
      "               \\tau_{ht} : 0.001072                                                            Horizontal tail thickness/chord ratio\n",
      "                  b_{ht} : 12.73                                                 [m]           Horizontal tail span\n",
      "              c_{attach} : 2.635                                                 [m]           HT Chord Where it is Mounted to the VT\n",
      "           c_{root_{ht}} : 3.696                                                 [m]           Horizontal tail root chord\n",
      "            c_{tip_{ht}} : 1.109                                                 [m]           Horizontal tail tip chord\n",
      "                  e_{ht} : 0.9894                                                              Oswald efficiency factor\n",
      "         f(\\lambda_{ht}) : 0.002027                                                            Empirical efficiency function of taper\n",
      "                  l_{ht} : 11.6                                                  [m]           Horizontal tail moment arm\n",
      "               m_{ratio} : 1.187                                                               Wing to Tail Lift Slope Ratio\n",
      "                  p_{ht} : 1.6                                                                 Substituted variable = 1 + 2*taper\n",
      "                  q_{ht} : 1.3                                                                 Substituted variable = 1 + taper\n",
      "             x_{CG_{ht}} : 32.67                                                 [m]           Horizontal tail CG location\n",
      "        y_{\\bar{c}_{ht}} : 3.447                                                 [m]           Spanwise location of mean aerodynamic chord\n",
      "\n",
      "                         | Mission.1/Aircraft.1/HorizontalTail.1/HorizontalTailNoStruct.1/Relax.1\n",
      "          C_{L_{ht,fCG}} : 1                                                                   HT CL During Max Forward CG\n",
      "          C_{L_{ht,max}} : 1                                                                   Max lift coefficient\n",
      "         \\alpha_{ht,max} : 1                                                                   Max angle of attack, htail\n",
      "               \\eta_{ht} : 1                                                                   Tail efficiency\n",
      "            \\lambda_{ht} : 1                                                                   Horizontal tail taper ratio\n",
      "      \\tan(\\Lambda_{ht}) : 1                                                                   tangent of horizontal tail sweep\n",
      "\n",
      "                         | Mission.1/Aircraft.1/HorizontalTail.1/Relax.1\n",
      "                  C_{ht} : 1                                                                   HT Weight Margin and Sensitivity Factor\n",
      "    \\cos(\\Lambda_{ht})^3 : 1                                                                   Cosine of tail sweep cubed\n",
      "              c_{d_{fh}} : 1                                                                   VT friction drag coefficient\n",
      "              c_{d_{ph}} : 1                                                                   VT pressure drag coefficient\n",
      "                  f_{ht} : 1                                                                   Rudder etc. fractional weight\n",
      "\n",
      "                         | Mission.1/Aircraft.1/HorizontalTail.1/WingBox.5\n",
      "                 I_{cap} : 2.651e-11                                                           Non-dim spar cap area moment of inertia\n",
      "     L_{ht_{rect_{out}}} : 1.056e+05                                             [N]           Rectangular HT load outboard\n",
      "           L_{ht_{rect}} : 1.79e+05                                              [N]           Rectangular HT load\n",
      "      L_{ht_{tri_{out}}} : 7.265e+04                                             [N]           Triangular HT load outboard\n",
      "            L_{ht_{tri}} : 2.089e+05                                             [N]           Triangular HT load\n",
      "               L_{shear} : 1.782e+05                                             [N]           Maximum shear load (at pin joint)\n",
      "                     M_r : 169                                                   [N]           Root moment per root chord\n",
      "             M_{r_{out}} : 1e+30                                                 [N]           Wing moment at pin joint\n",
      "                N_{lift} : 1                                                                   Wing loading multiplier\n",
      "                 W_{cap} : 347.8                                                 [N]           Weight of spar caps\n",
      "              W_{struct} : 514.5                                                 [N]           Structural weight\n",
      "                 W_{web} : 166.7                                                 [N]           Weight of shear web\n",
      "                     \\nu : 0.8225                                                              Dummy variable = $(t^2 + t + 1)/(t+1)^2$\n",
      "             \\pi_{M-fac} : 1                                                                   Pi-tail bending structural factor\n",
      "              \\rho_{cap} : 2700                                                  [kg/m³]       Density of spar cap material\n",
      "              \\rho_{web} : 2700                                                  [kg/m³]       Density of shear web material\n",
      "      \\sigma_{max,shear} : 1.67e+08                                              [Pa]          Allowable shear stress\n",
      "            \\sigma_{max} : 2.5e+08                                               [Pa]          Allowable tensile stress\n",
      "            b_{ht_{out}} : 3.753                                                 [m]           Horizontal tail outboard half-span\n",
      "                       g : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                     r_h : 0.75                                                                Fractional wing thickness at spar web\n",
      "                 r_{w/c} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "                 t_{cap} : 0.000163                                                            Non-dim. spar cap thickness\n",
      "                 t_{web} : 0.0486                                                              Non-dim. shear web thickness\n",
      "                   taper : 0.3                                                                 Taper ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/HorizontalTail.1/WingBox.5/Relax.1\n",
      "              \\rho_{cap} : 1                                                                   Density of spar cap material\n",
      "              \\rho_{web} : 1                                                                   Density of shear web material\n",
      "      \\sigma_{max,shear} : 1                                                                   Allowable shear stress\n",
      "            \\sigma_{max} : 1                                                                   Allowable tensile stress\n",
      "                       g : 1                                                                   Gravitational acceleration\n",
      "                     r_h : 1                                                                   Fractional wing thickness at spar web\n",
      "                 r_{w/c} : 1                                                                   Wingbox width-to-chord ratio\n",
      "                   taper : 1                                                                   Taper ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/LandingGear.1\n",
      "                       B : 17.19                                                 [m]           Landing gear base\n",
      "                  C_{lg} : 1                                                                   Landing Gear Weight Margin/Sens Factor\n",
      "                       E : 205                                                   [GPa]         Modulus of elasticity, 4340 steel\n",
      "                E_{land} : 3.526e+05                                             [J]           Max KE to be absorbed in landing\n",
      "                 F_{w_m} : 1.008e+04                                                           Weight factor (main)\n",
      "                 F_{w_n} : 298.2                                                               Weight factor (nose)\n",
      "                     I_m : 2.878e-06                                             [m⁴]          Area moment of inertia (main strut)\n",
      "                     I_n : 8.96e-08                                              [m⁴]          Area moment of inertia (nose strut)\n",
      "                       K : 2                                                                   Column effective length factor\n",
      "                     L_m : 8.346e+05                                             [N]           Max static load through main gear\n",
      "                     L_n : 6.867e+04                                             [N]           Min static load through nose gear\n",
      "             L_{n_{dyn}} : 3.844e+04                                             [N]           Dyn. braking load, nose gear\n",
      "                 L_{w_m} : 2.086e+05                                             [N]           Static load per wheel (main)\n",
      "                 L_{w_n} : 3.434e+04                                             [N]           Static load per wheel (nose)\n",
      "                     N_s : 2                                                                   Factor of safety\n",
      "                  S_{sa} : 0.2112                                                [m]           Stroke of the shock absorber\n",
      "                       T : 2.611                                                 [m]           Main landing gear track\n",
      "                  W_{lg} : 1.641e+04                                             [N]           Weight of landing gear\n",
      "                  W_{mg} : 1.553e+04                                             [N]           Weight of main gear\n",
      "                  W_{ms} : 446.2                                                 [N]           Weight of main struts\n",
      "                  W_{mw} : 2927                                                  [N]           Weight of main wheels (per strut)\n",
      "                  W_{ng} : 881.9                                                 [N]           Weight of nose gear\n",
      "                  W_{ns} : 24.26                                                 [N]           Weight of nose strut\n",
      "                  W_{nw} : 343.1                                                 [N]           Weight of nose wheels (total)\n",
      "                W_{wa,m} : 329                                                   [lbf]         Wheel assembly weight for single main gear wheel\n",
      "                W_{wa,n} : 38.56                                                 [lbf]         Wheel assembly weight for single nose gear wheel\n",
      "              \\Delta x_m : 1.831                                                 [m]           Distance b/w main gear and CG\n",
      "              \\Delta x_n : 22.25                                                 [m]           Distance b/w nose gear and CG\n",
      "                  \\eta_s : 0.8                                                                 Shock absorber efficiency\n",
      "            \\lambda_{LG} : 2.5                                                                 Ratio of max to static load\n",
      "               \\rho_{st} : 7850                                                  [kg/m³]       Density of 4340 Steel\n",
      "            \\sigma_{y_c} : 4.7e+08                                               [Pa]          Compressive yield strength 4340 steel\n",
      "            \\tan(\\gamma) : 0.08749                                                             Dihedral angle\n",
      "              \\tan(\\phi) : 0.2679                                                              Angle b/w main gear and CG\n",
      "        \\tan(\\phi_{min}) : 0.2679                                                              Lower bound on phi\n",
      "              \\tan(\\psi) : 1.963                                                               Tip over angle\n",
      "        \\tan(\\psi_{max}) : 1.963                                                               Upper bound on psi\n",
      "      \\tan(\\theta_{max}) : 0.2679                                                              Max rotation angle\n",
      "             d_{nacelle} : 1e+30                                                 [m]           Nacelle diameter\n",
      "                d_{oleo} : 0.4253                                                [m]           Diameter of oleo shock absorber\n",
      "                 d_{t_m} : 48.29                                                 [in]          Diameter of main gear tires\n",
      "                 d_{t_n} : 38.63                                                 [in]          Diameter of nose gear tires\n",
      "               f_{add,m} : 1.5                                                                 Proportional added weight, main\n",
      "               f_{add,n} : 1.5                                                                 Proportional added weight, nose\n",
      "                       g : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                h_{hold} : 1                                                     [m]           Hold height\n",
      "                     l_m : 1.305                                                 [m]           Length of main gear\n",
      "                     l_n : 0.6911                                                [m]           Length of nose gear\n",
      "                l_{oleo} : 0.5281                                                [m]           Length of oleo shock absorber\n",
      "                  n_{mg} : 2                                                                   Number of main gear struts\n",
      "                 n_{wps} : 2                                                                   Number of wheels per strut\n",
      "                p_{oleo} : 1800                                                  [lbf/in²]     Oleo pressure\n",
      "                     r_m : 0.03601                                               [m]           Radius of main gear struts\n",
      "                     r_n : 0.01983                                               [m]           Radius of nose gear struts\n",
      "                     t_m : 0.01962                                               [m]           Thickness of main gear strut wall\n",
      "                     t_n : 0.003659                                              [m]           Thickness of nose gear strut wall\n",
      "             t_{nacelle} : 0.15                                                  [m]           Nacelle thickness\n",
      "                 w_{t_m} : 0.4631                                                [m]           Width of main tires\n",
      "                 w_{t_n} : 0.3705                                                [m]           Width of nose tires\n",
      "                 w_{ult} : 10                                                    [ft/s]        Ultimate velocity of descent\n",
      "                     x_m : 22.19                                                 [m]           x-location of main gear\n",
      "                     x_n : 5                                                     [m]           x-location of nose gear\n",
      "             x_{CG_{lg}} : 21.27                                                 [m]           Landing gear CG\n",
      "                  x_{up} : 27.06                                                 [m]           Fuselage upsweep point\n",
      "                     y_m : 1.305                                                 [m]           y-location of main gear (symmetric)\n",
      "                  z_{CG} : 2                                                     [m]           CG height relative to bottom of fuselage\n",
      "                z_{wing} : 0.5                                                   [m]           Height of wing relative to base of fuselage\n",
      "\n",
      "                         | Mission.1/Aircraft.1/LandingGear.1/Relax.1\n",
      "                  C_{lg} : 1                                                                   Landing Gear Weight Margin/Sens Factor\n",
      "                       E : 1                                                                   Modulus of elasticity, 4340 steel\n",
      "                       K : 1                                                                   Column effective length factor\n",
      "                     N_s : 1                                                                   Factor of safety\n",
      "                  \\eta_s : 1                                                                   Shock absorber efficiency\n",
      "            \\lambda_{LG} : 1                                                                   Ratio of max to static load\n",
      "               \\rho_{st} : 1                                                                   Density of 4340 Steel\n",
      "            \\sigma_{y_c} : 1                                                                   Compressive yield strength 4340 steel\n",
      "            \\tan(\\gamma) : 1                                                                   Dihedral angle\n",
      "        \\tan(\\phi_{min}) : 1                                                                   Lower bound on phi\n",
      "        \\tan(\\psi_{max}) : 1                                                                   Upper bound on psi\n",
      "      \\tan(\\theta_{max}) : 1                                                                   Max rotation angle\n",
      "               f_{add,m} : 1                                                                   Proportional added weight, main\n",
      "               f_{add,n} : 1                                                                   Proportional added weight, nose\n",
      "                       g : 1                                                                   Gravitational acceleration\n",
      "                h_{hold} : 1                                                                   Hold height\n",
      "                  n_{mg} : 1                                                                   Number of main gear struts\n",
      "                 n_{wps} : 1                                                                   Number of wheels per strut\n",
      "                p_{oleo} : 1                                                                   Oleo pressure\n",
      "             t_{nacelle} : 1                                                                   Nacelle thickness\n",
      "                 w_{ult} : 1                                                                   Ultimate velocity of descent\n",
      "                  z_{CG} : 1                                                                   CG height relative to bottom of fuselage\n",
      "                z_{wing} : 1                                                                   Height of wing relative to base of fuselage\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Relax.1\n",
      "       BLI_{wakebenefit} : 1                                                                   Wake Drag Reduction from BLI Wake Ingestion\n",
      "              C_{engsys} : 1                                                                   Engine System Weight Margin/Sens Factor\n",
      "              D_{reduct} : 1                                                                   BLI Drag Reduction Factor\n",
      "        D_{wakefraction} : 1                                                                   Percent of Total Drag From Wake Dissipation\n",
      "                 M_{min} : 1                                                                   Minimum Cruise Mach Number\n",
      "                SM_{min} : 1                                                                   Minimum Static Margin\n",
      "                  V_{mn} : 1                                                                   Maneuvering speed\n",
      "                  V_{ne} : 1                                                                   Never-exceed speed\n",
      "           \\Delta x_{CG} : 1                                                                   Max CG Travel Range\n",
      "              \\rho_{T/O} : 1                                                                   Air density at takeoff\n",
      "      f_{L_{total/wing}} : 1                                                                   Total lift as a percentage of wing lift\n",
      "                f_{eadd} : 1                                                                   Additional Engine Weight Fraction\n",
      "          f_{fuel_{res}} : 1                                                                   Fuel Reserve Fraction\n",
      "              f_{hpesys} : 1                                                                   Power Systems Weight Fraction\n",
      "               f_{pylon} : 1                                                                   Pylong Weight Fraction\n",
      "            f_{wingfuel} : 1                                                                   Fraction of fuel stored in wing tanks\n",
      "               n_{aisle} : 1                                                                   Number of Aisles\n",
      "                 n_{eng} : 1                                                                   Number of Engines\n",
      "                  n_{vt} : 1                                                                   Number of Vertical Tails\n",
      "         r_{S_{nacelle}} : 1                                                                   Nacelle and Pylon Wetted Area\n",
      "         r_{v_{nacelle}} : 1                                                                   Incoming Nacelle Velocity Ratio\n",
      "            x_{CG_{min}} : 1                                                                   Maximum Forward CG\n",
      "\n",
      "                         | Mission.1/Aircraft.1/VerticalTail.1\n",
      "                  C_{VT} : 1                                                                   VT Weight Margin and Sensitivity\n",
      "                N_{spar} : 1                                                                   Number of Spars in Each VT Carrying Stress in 1 in 20 Case\n",
      "                  W_{vt} : 1351                                                  [N]           Total VT System Weight\n",
      "    \\cos(\\Lambda_{vt})^3 : 0.7444                                                              Cosine of tail sweep cubed\n",
      "              c_{d_{fv}} : 0.006                                                               VT friction drag coefficient\n",
      "              c_{d_{pv}} : 0.0035                                                              VT pressure drag coefficient\n",
      "                  f_{VT} : 0.4                                                                 VT Fractional Weight\n",
      "\n",
      "                         | Mission.1/Aircraft.1/VerticalTail.1/Relax.1\n",
      "                  C_{VT} : 1                                                                   VT Weight Margin and Sensitivity\n",
      "                N_{spar} : 1                                                                   Number of Spars in Each VT Carrying Stress in 1 in 20 Case\n",
      "    \\cos(\\Lambda_{vt})^3 : 1                                                                   Cosine of tail sweep cubed\n",
      "              c_{d_{fv}} : 1                                                                   VT friction drag coefficient\n",
      "              c_{d_{pv}} : 1                                                                   VT pressure drag coefficient\n",
      "                  f_{VT} : 1                                                                   VT Fractional Weight\n",
      "\n",
      "                         | Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1\n",
      "                  A_{vt} : 2.2                                                                 Vertical tail aspect ratio\n",
      "              C_{D_{wm}} : 0.5                                                                 Windmill drag coefficient\n",
      "           C_{L_{vt,EO}} : 0.2792                                                              Vertical tail lift coefficient (engine out)\n",
      "          C_{L_{vt,max}} : 2.6                                                                 Max lift coefficient\n",
      "          C_{L_{vt,yaw}} : 2.21                                                                VT CL at rotation\n",
      "                  D_{wm} : 8265                                                  [N]           Engine out windmill drag\n",
      "              I_{z, max} : 6.617e+06                                             [kg·m²]       Aircraft Z-axis Moment of Inertia\n",
      "               L_{vt,EO} : 5499                                                  [N]           Vertical tail lift in engine out\n",
      "            L_{vt_{max}} : 2.164e+05                                             [N]           Maximum load for structural sizing\n",
      "                  S_{vt} : 6.561                                                 [m²]          Vertical tail reference area\n",
      "                     T_e : 4.451e+04                                             [N]           Thrust per engine at takeoff\n",
      "                     V_1 : 70                                                    [m/s]         Minimum takeoff velocity\n",
      "                V_{land} : 72                                                    [m/s]         Aircraft Landing Speed\n",
      "            V_{vt_{min}} : 0.001                                                               Minimum Vertical Tail Volume Coefficient\n",
      "                  V_{vt} : 0.02429                                                             Vertical Tail Volume Coefficient\n",
      "    \\Delta x_{lead_{vt}} : 9.646                                                 [m]           Distance from CG to vertical tail leading edge\n",
      "   \\Delta x_{trail_{vt}} : 12.3                                                  [m]           Distance from CG to vertical tail trailing edge\n",
      "            \\bar{c}_{vt} : 1.894                                                 [m]           Vertical tail mean aero chord\n",
      "           \\dot{r}_{req} : 0.1475                                                [1/s²]        Required Yaw Rate at Landing\n",
      "            \\lambda_{vt} : 0.3                                                                 Vertical tail taper ratio\n",
      "                   \\mu_0 : 1.8e-05                                               [N·s/m²]      Dynamic viscosity (SL)\n",
      "               \\rho_{TO} : 1.225                                                 [kg/m³]       Air density (SL))\n",
      "      \\tan(\\Lambda_{vt}) : 0.4663                                                              Tangent of leading edge sweep\n",
      "               \\tau_{vt} : 0.14                                                                Vertical tail thickness/chord ratio\n",
      "                  b_{vt} : 3.799                                                 [m]           Vertical tail span\n",
      "           c_{l_{vt,EO}} : 0.5                                                                 Sectional lift force coefficient (engine out)\n",
      "           c_{root_{vt}} : 2.657                                                 [m]           Vertical tail root chord\n",
      "            c_{tip_{vt}} : 0.797                                                 [m]           Vertical tail tip chord\n",
      "                  e_{vt} : 0.8                                                                 Span efficiency of vertical tail\n",
      "                  l_{vt} : 10.6                                                  [m]           Vertical tail moment arm\n",
      "                  p_{vt} : 1.6                                                                 Substituted variable = 1 + 2*taper\n",
      "                  q_{vt} : 1.3                                                                 Substituted variable = 1 + taper\n",
      "             x_{CG_{vt}} : 31.34                                                 [m]           x-location of tail CG\n",
      "        y_{\\bar{c}_{vt}} : 1.029                                                 [m]           Spanwise location of mean aerodynamic chord\n",
      "                 y_{eng} : 1.305                                                 [m]           Engine moment arm\n",
      "        z_{\\bar{c}_{vt}} : 1.029                                                 [m]           Vertical location of mean aerodynamic chord\n",
      "\n",
      "                         | Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1/Relax.1\n",
      "                  A_{vt} : 1                                                                   Vertical tail aspect ratio\n",
      "              C_{D_{wm}} : 1                                                                   Windmill drag coefficient\n",
      "          C_{L_{vt,max}} : 1                                                                   Max lift coefficient\n",
      "                     V_1 : 1                                                                   Minimum takeoff velocity\n",
      "                V_{land} : 1                                                                   Aircraft Landing Speed\n",
      "            V_{vt_{min}} : 1                                                                   Minimum Vertical Tail Volume Coefficient\n",
      "           \\dot{r}_{req} : 1                                                                   Required Yaw Rate at Landing\n",
      "            \\lambda_{vt} : 1                                                                   Vertical tail taper ratio\n",
      "                   \\mu_0 : 1                                                                   Dynamic viscosity (SL)\n",
      "               \\rho_{TO} : 1                                                                   Air density (SL))\n",
      "      \\tan(\\Lambda_{vt}) : 1                                                                   Tangent of leading edge sweep\n",
      "           c_{l_{vt,EO}} : 1                                                                   Sectional lift force coefficient (engine out)\n",
      "                  e_{vt} : 1                                                                   Span efficiency of vertical tail\n",
      "\n",
      "                         | Mission.1/Aircraft.1/VerticalTail.1/WingBox.4\n",
      "                 AR_{vt} : 4.4                                                                 Vertical tail aspect ratio (double span)\n",
      "                 I_{cap} : 1.091e-05                                                           Non-dim spar cap area moment of inertia\n",
      "                     M_r : 2.751e+05                                             [N]           Root moment per root chord\n",
      "                N_{lift} : 1                                                                   Wing loading multiplier\n",
      "                 W_{cap} : 1809                                                  [N]           Weight of spar caps\n",
      "              W_{struct} : 965                                                   [N]           Structural weight\n",
      "                 W_{web} : 120.9                                                 [N]           Weight of shear web\n",
      "                     \\nu : 0.8225                                                              Dummy variable = $(t^2 + t + 1)/(t+1)^2$\n",
      "              \\rho_{cap} : 2700                                                  [kg/m³]       Density of spar cap material\n",
      "              \\rho_{web} : 2700                                                  [kg/m³]       Density of shear web material\n",
      "      \\sigma_{max,shear} : 1.67e+08                                              [Pa]          Allowable shear stress\n",
      "            \\sigma_{max} : 2.5e+08                                               [Pa]          Allowable tensile stress\n",
      "                       g : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                     r_h : 0.75                                                                Fractional wing thickness at spar web\n",
      "                 r_{w/c} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "                 t_{cap} : 0.002748                                                            Non-dim. spar cap thickness\n",
      "                 t_{web} : 0.0008743                                                           Non-dim. shear web thickness\n",
      "                   taper : 0.3                                                                 Taper ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/VerticalTail.1/WingBox.4/Relax.1\n",
      "              \\rho_{cap} : 1                                                                   Density of spar cap material\n",
      "              \\rho_{web} : 1                                                                   Density of shear web material\n",
      "      \\sigma_{max,shear} : 1                                                                   Allowable shear stress\n",
      "            \\sigma_{max} : 1                                                                   Allowable tensile stress\n",
      "                       g : 1                                                                   Gravitational acceleration\n",
      "                     r_h : 1                                                                   Fractional wing thickness at spar web\n",
      "                 r_{w/c} : 1                                                                   Wingbox width-to-chord ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Wing.1\n",
      "                C_{wing} : 1                                                                   Wing Weight Margin and Sensitivity Factor\n",
      "               TipReduct : 1                                                                   Induced Drag Reduction Factor from Wing Tip Devices\n",
      "                W_{wing} : 1.047e+05                                             [N]           Wing System Weight\n",
      "    \\Delta x_{AC_{wing}} : 1.238                                                 [m]           Wing Aerodynamic Center Shift\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Wing.1/Relax.1\n",
      "                C_{wing} : 1                                                                   Wing Weight Margin and Sensitivity Factor\n",
      "               TipReduct : 1                                                                   Induced Drag Reduction Factor from Wing Tip Devices\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Wing.1/WingBox.3\n",
      "                 I_{cap} : 1.939e-05                                                           Non-dim spar cap area moment of inertia\n",
      "                     M_r : 2.201e+06                                             [N]           Root moment per root chord\n",
      "                N_{lift} : 3                                                                   Wing loading multiplier\n",
      "                 W_{cap} : 6.5e+04                                               [N]           Weight of spar caps\n",
      "              W_{struct} : 6.791e+04                                             [N]           Structural weight\n",
      "                 W_{web} : 2918                                                  [N]           Weight of shear web\n",
      "                     \\nu : 0.8867                                                              Dummy variable = $(t^2 + t + 1)/(t+1)^2$\n",
      "              \\rho_{cap} : 2700                                                  [kg/m³]       Density of spar cap material\n",
      "              \\rho_{web} : 2700                                                  [kg/m³]       Density of shear web material\n",
      "      \\sigma_{max,shear} : 1.67e+08                                              [Pa]          Allowable shear stress\n",
      "            \\sigma_{max} : 2.5e+08                                               [Pa]          Allowable tensile stress\n",
      "                       g : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                     r_h : 0.75                                                                Fractional wing thickness at spar web\n",
      "                 r_{w/c} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "                 t_{cap} : 0.004523                                                            Non-dim. spar cap thickness\n",
      "                 t_{web} : 0.000919                                                            Non-dim. shear web thickness\n",
      "                   taper : 0.15                                                                Taper ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Wing.1/WingBox.3/Relax.1\n",
      "              \\rho_{cap} : 1                                                                   Density of spar cap material\n",
      "              \\rho_{web} : 1                                                                   Density of shear web material\n",
      "      \\sigma_{max,shear} : 1                                                                   Allowable shear stress\n",
      "            \\sigma_{max} : 1                                                                   Allowable tensile stress\n",
      "                       g : 1                                                                   Gravitational acceleration\n",
      "                     r_h : 1                                                                   Fractional wing thickness at spar web\n",
      "                 r_{w/c} : 1                                                                   Wingbox width-to-chord ratio\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Wing.1/WingNoStruct.1\n",
      "                      AR : 12.48                                                               Wing aspect ratio\n",
      "                A_{rect} : 36                                                    [m²]          Rectangular Wing Area\n",
      "                 A_{tri} : 1e+30                                                 [m²]          Triangular Wing Area\n",
      "           C_{L_{w,max}} : 2.269                                                               Max lift coefficient, wing\n",
      "                FuelFrac : 0.9                                                                 Usability Factor of Max Fuel Volume\n",
      "                 L_{max} : 2.268e+06                                             [N]           Maximum load\n",
      "                       S : 138                                                   [m²]          Wing area\n",
      "           V_{fuel, max} : 20.78                                                 [m³]          Available fuel volume\n",
      "         W_{fuel_{wing}} : 1.21e+05                                              [N]           Fuel weight\n",
      "           \\cos(\\Lambda) : 0.9734                                                              Cosine of quarter-chord sweep angle\n",
      "                    \\eta : 0.97                                                                Lift efficiency (diff b/w sectional, actual lift)\n",
      "                 \\lambda : 0.15                                                                Wing taper ratio\n",
      "                  \\rho_0 : 1.225                                                 [kg/m³]       Air density (0 ft)\n",
      "             \\rho_{fuel} : 817                                                   [kg/m³]       Density of fuel\n",
      "           \\tan(\\Lambda) : 0.2352                                                              Tangent of quarter-chord sweep angle\n",
      "                    \\tau : 0.1473                                                              Wing thickness/chord ratio\n",
      "            \\tau_{max_w} : 0.1473                                                              Max allowed wing thickness\n",
      "                       b : 41.5                                                  [m]           Wing span\n",
      "                 b_{max} : 42.67                                                 [m]           Max Wing Span\n",
      "                c_{root} : 5.783                                                 [m]           Wing root chord\n",
      "                 c_{tip} : 0.8674                                                [m]           Wing tip chord\n",
      "                       e : 0.9461                                                              Oswald efficiency factor\n",
      "            f(\\lambda_w) : 0.004563                                                            Empirical efficiency function of taper\n",
      "             f_{aileron} : 0.04                                                                Aileron Fractional Weight\n",
      "                f_{flap} : 0.2                                                                 Flap Fractional Weight\n",
      "                f_{lete} : 0.1                                                                 Lete Fractional Weight\n",
      "                f_{ribs} : 0.15                                                                Rib Fractional Weight\n",
      "                f_{slat} : 0.001                                                               Slat Fractional Weight\n",
      "             f_{spoiler} : 0.02                                                                Spoiler Fractional Weight\n",
      "                f_{watt} : 0.03                                                                Watt Fractional Weight\n",
      "                       g : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                     mac : 3.931                                                 [m]           Mean aerodynamic chord (wing)\n",
      "                       p : 1.3                                                                 Substituted variable = 1 + 2*taper\n",
      "                       q : 1.15                                                                Substituted variable = 1 + taper\n",
      "                     wwn : 0.5                                                                 Wingbox-width-to-chord ratio\n",
      "                     x_w : 20.96                                                 [m]           Position of wing aerodynamic center\n",
      "                 y_{mac} : 12.24                                                 [m]           Spanwise location of mean aerodynamic chord\n",
      "\n",
      "                         | Mission.1/Aircraft.1/Wing.1/WingNoStruct.1/Relax.1\n",
      "           C_{L_{w,max}} : 1                                                                   Max lift coefficient, wing\n",
      "                FuelFrac : 1                                                                   Usability Factor of Max Fuel Volume\n",
      "           \\cos(\\Lambda) : 1                                                                   Cosine of quarter-chord sweep angle\n",
      "                    \\eta : 1                                                                   Lift efficiency (diff b/w sectional, actual lift)\n",
      "                  \\rho_0 : 1                                                                   Air density (0 ft)\n",
      "             \\rho_{fuel} : 1                                                                   Density of fuel\n",
      "           \\tan(\\Lambda) : 1                                                                   Tangent of quarter-chord sweep angle\n",
      "            \\tau_{max_w} : 1                                                                   Max allowed wing thickness\n",
      "                 b_{max} : 1                                                                   Max Wing Span\n",
      "             f_{aileron} : 1                                                                   Aileron Fractional Weight\n",
      "                f_{flap} : 1                                                                   Flap Fractional Weight\n",
      "                f_{lete} : 1                                                                   Lete Fractional Weight\n",
      "                f_{ribs} : 1                                                                   Rib Fractional Weight\n",
      "                f_{slat} : 1                                                                   Slat Fractional Weight\n",
      "             f_{spoiler} : 1                                                                   Spoiler Fractional Weight\n",
      "                f_{watt} : 1                                                                   Watt Fractional Weight\n",
      "                       g : 1                                                                   Gravitational acceleration\n",
      "                     wwn : 1                                                                   Wingbox-width-to-chord ratio\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1\n",
      "              P_{excess} : [ 1.04e+07  1.12e+07  5.08e+06                        [W]           Excess Power During Climb\n",
      "                             1.04e+07  1.12e+07  5.08e+06  ]\n",
      "                      RC : [ 3.17e+03  3.43e+03  1.56e+03                        [ft/min]      Rate of Climb/Descent\n",
      "                             3.17e+03  3.43e+03  1.56e+03  ]\n",
      "               R_{climb} : [ 27.7      28.9      61.6                            [nmi]         Down Range Covered in Each Climb Segment\n",
      "                             27.7      28.9      61.6      ]\n",
      "                  \\theta : [ 0.0762    0.0731    0.0343                                        Aircraft Climb Angle\n",
      "                             0.0762    0.0731    0.0343    ]\n",
      "                    dhft : [ 1.28e+04  1.28e+04  1.28e+04                        [ft]          Change in Altitude Per Climb Segment [feet]\n",
      "                             1.28e+04  1.28e+04  1.28e+04  ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2\n",
      "                     C_D : [ 0.0155    0.0187    0.0246                                        Total Aircraft Drag Coefficient\n",
      "                             0.0155    0.0187    0.0246    ]\n",
      "         C_{d_{nacelle}} : [ 0.000743  0.000743  0.000743                                      Nacelle Drag Coeffecient\n",
      "                             0.000743  0.000743  0.000743  ]\n",
      "         C_{f_{nacelle}} : [ 0.0116    0.012     0.0128                                        Nacelle Drag Coefficient\n",
      "                             0.0116    0.012     0.0128    ]\n",
      "                       D : [ 3.96e+04  3.92e+04  3e+04                           [N]           Total Aircraft Drag\n",
      "                             3.96e+04  3.92e+04  3e+04     ]\n",
      "             D_{nacelle} : [ 1.9e+03   1.56e+03  908                             [N]           Drag On One Nacelle\n",
      "                             1.9e+03   1.56e+03  908       ]\n",
      "                F_{fuel} : [ 0.966     0.933     0.89                                          Percent Fuel Remaining (end of segment)\n",
      "                             0.966     0.933     0.89      ]\n",
      "                     L/D : [ 16.4      16.4      21.3                                          Lift-to-Drag Ratio\n",
      "                             16.4      16.4      21.3      ]\n",
      "               L_{total} : [ 6.54e+05  6.5e+05   6.43e+05                        [N]           Total lift\n",
      "                             6.54e+05  6.5e+05   6.43e+05  ]\n",
      "               P_{cabin} : [ 7.5e+04   7.5e+04   7.5e+04                         [Pa]          Cabin Air Pressure\n",
      "                             7.5e+04   7.5e+04   7.5e+04   ]\n",
      "         R_{e_{nacelle}} : [ 8.16e+06  6.94e+06  4.93e+06                                      Nacelle Reynolds Number\n",
      "                             8.16e+06  6.94e+06  4.93e+06  ]\n",
      "                      SM : [ 0.11      0.11      0.109                                         Stability Margin of Aircraft\n",
      "                             0.11      0.11      0.109     ]\n",
      "               T_{cabin} : [ 297       297       297                             [K]           Cabin Air Temperature\n",
      "                             297       297       297       ]\n",
      "                     V_2 : [ 212       238       231                             [m/s]         Interior Nacelle Flow Velcoity\n",
      "                             212       238       231       ]\n",
      "       V_{nacelle_ratio} : [ 0.85      0.85      0.85                                          Vnle/Vinf\n",
      "                             0.85      0.85      0.85      ]\n",
      "             V_{nacelle} : [ 196       221       214                             [m/s]         Incoming Nacelle Flow Velocity\n",
      "                             196       221       214       ]\n",
      "               V_{stall} : [ 120       120       120                             [kt]          Aircraft Stall Speed\n",
      "                             120       120       120       ]\n",
      "          W_{Load_{max}} : [ 6.66e+03  6.66e+03  6.66e+03                        [N/m²]        Max Wing Loading\n",
      "                             6.66e+03  6.66e+03  6.66e+03  ]\n",
      "                W_{Load} : [ 4.19e+03  4.16e+03  4.12e+03                        [N/m²]        Wing Loading\n",
      "                             4.19e+03  4.16e+03  4.12e+03  ]\n",
      "                 W_{avg} : [ 1.46e+05  1.45e+05  1.44e+05                        [lbf]         Geometric Average of Segment Start and End Weight\n",
      "                             1.46e+05  1.45e+05  1.44e+05  ]\n",
      "                W_{buoy} : [ 887       862       786                             [lbf]         Buoyancy Weight\n",
      "                             887       862       786       ]\n",
      "                W_{burn} : [ 696       667       887                             [lbf]         Segment Fuel Burn Weight\n",
      "                             696       667       887       ]\n",
      "                 W_{end} : [ 1.44e+05  1.44e+05  1.43e+05                        [lbf]         Segment End Weight\n",
      "                             1.44e+05  1.44e+05  1.43e+05  ]\n",
      "               W_{start} : [ 1.45e+05  1.44e+05  1.44e+05                        [lbf]         Segment Start Weight\n",
      "                             1.45e+05  1.44e+05  1.44e+05  ]\n",
      "            \\rho_{cabin} : [ 0.88      0.88      0.88                            [kg/m³]       Cabin Air Density\n",
      "                             0.88      0.88      0.88      ]\n",
      "           r_{v_{nsurf}} : [ 0.888     0.888     0.888                                         Intermediate Nacelle Drag Parameter\n",
      "                             0.888     0.888     0.888     ]\n",
      "                     thr : [ 0.0674    0.0623    0.137                           [hr]          Segment Flight Time in Hours\n",
      "                             0.0674    0.0623    0.137     ]\n",
      "                    tmin : [ 4.04      3.74      8.22                            [min]         Segment Flight Time in Minutes\n",
      "                             4.04      3.74      8.22      ]\n",
      "                  x_{AC} : [ 22        22        22                              [m]           Aerodynamic Center of Aircraft\n",
      "                             22        22        22        ]\n",
      "                  x_{CG} : [ 20.4      20.4      20.4                            [m]           Center of Gravity of Aircraft\n",
      "                             20.4      20.4      20.4      ]\n",
      "                  x_{NP} : [ 1.57      1.57      1.57                            [m]           Neutral Point of Aircraft\n",
      "                             1.57      1.57      1.57      ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/FuselagePerformance.2\n",
      "            C_{D_{fuse}} : [ 0.0181    0.0181    0.0181                                        Fuselage Drag Coefficient\n",
      "                             0.0181    0.0181    0.0181    ]\n",
      "                D_{fuse} : [ 1.5e+04   1.74e+04  1.07e+04                        [N]           Fuselage Drag\n",
      "                             1.5e+04   1.74e+04  1.07e+04  ]\n",
      "                L_{fuse} : [ 1.07e+05  1.06e+05  1.05e+05                        [N]           Fuselage Lift\n",
      "                             1.07e+05  1.06e+05  1.05e+05  ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/HorizontalTailPerformance.2\n",
      "            C_{D_{0,ht}} : [ 0.00228   0.0028    0.00276                                       Horizontal tail parasitic drag coefficient\n",
      "                             0.00228   0.0028    0.00276   ]\n",
      "              C_{D_{ht}} : [ 0.00229   0.00281   0.00277                                       Horizontal tail drag coefficient\n",
      "                             0.00229   0.00281   0.00277   ]\n",
      "     C_{L_{\\alpha,ht_0}} : [ 6.28      6.28      6.28                                          Isolated lift curve slope (htail)\n",
      "                             6.28      6.28      6.28      ]\n",
      "       C_{L_{\\alpha,ht}} : [ 0.0759    0.0727    0.072                                         Lift curve slope (htail)\n",
      "                             0.0759    0.0727    0.072     ]\n",
      "              C_{L_{ht}} : [ 0.01      0.01      0.01                                          Lift coefficient (htail)\n",
      "                             0.01      0.01      0.01      ]\n",
      "                  D_{ht} : [ 1.29e+03  1.31e+03  750                             [N]           Horizontal tail drag\n",
      "                             1.29e+03  1.31e+03  750       ]\n",
      "                  L_{ht} : [ 5.66e+03  4.66e+03  2.71e+03                        [N]           Horizontal tail downforce\n",
      "                             5.66e+03  4.66e+03  2.71e+03  ]\n",
      "                Re_{c_h} : [ 1.46e+07  1.24e+07  8.81e+06                                      Cruise Reynolds number (Horizontal tail)\n",
      "                             1.46e+07  1.24e+07  8.81e+06  ]\n",
      "             \\alpha_{ht} : [ 0.132     0.137     0.139                                         Horizontal tail angle of attack\n",
      "                             0.132     0.137     0.139     ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/Relax.1\n",
      "               V_{stall} : [ 1         1         1                                             Aircraft Stall Speed\n",
      "                             1         1         1         ]\n",
      "          W_{Load_{max}} : [ 1         1         1                                             Max Wing Loading\n",
      "                             1         1         1         ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/VerticalTailPerformance.2\n",
      "             C_{D_{vis}} : [ 0.0158    0.015     0.0141                                        Viscous drag coefficient\n",
      "                             0.0158    0.015     0.0141    ]\n",
      "                  D_{vt} : [ 1.92e+03  1.5e+03   819                             [N]           Vertical tail viscous drag, cruise\n",
      "                             1.92e+03  1.5e+03   819       ]\n",
      "                 Re_{vt} : [ 1.05e+07  8.92e+06  6.33e+06                                      Vertical tail reynolds number, cruise\n",
      "                             1.05e+07  8.92e+06  6.33e+06  ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/WingPerformance.2\n",
      "             C_{D_{i_w}} : [ 0.00138   0.00201   0.00582                                       Wing induced drag coefficient\n",
      "                             0.00138   0.00201   0.00582   ]\n",
      "             C_{D_{p_w}} : [ 0.00501   0.00514   0.00699                                       Wing parasitic drag coefficient\n",
      "                             0.00501   0.00514   0.00699   ]\n",
      "        C_{L_{\\alpha,w}} : [ 6.31      7.16      7.37                                          Lift curve slope, wing\n",
      "                             6.31      7.16      7.37      ]\n",
      "                   C_{L} : [ 0.226     0.273     0.465                                         Lift coefficient, wing\n",
      "                             0.226     0.273     0.465     ]\n",
      "                 C_{d_w} : [ 0.00639   0.00714   0.0128                                        Drag coefficient, wing\n",
      "                             0.00639   0.00714   0.0128    ]\n",
      "                D_{wing} : [ 1.63e+04  1.5e+04   1.57e+04                        [N]           Wing drag\n",
      "                             1.63e+04  1.5e+04   1.57e+04  ]\n",
      "                     L_w : [ 5.47e+05  5.44e+05  5.38e+05                        [N]           Wing lift\n",
      "                             5.47e+05  5.44e+05  5.38e+05  ]\n",
      "                    Re_w : [ 2.17e+07  1.85e+07  1.31e+07                                      Reynolds number (wing)\n",
      "                             2.17e+07  1.85e+07  1.31e+07  ]\n",
      "            \\Delta L_{o} : [ 2.99e+04  2.97e+04  2.94e+04                        [N]           Center wing lift loss\n",
      "                             2.99e+04  2.97e+04  2.94e+04  ]\n",
      "            \\Delta L_{t} : [ 149       148       147                             [N]           Wing tip lift loss\n",
      "                             149       148       147       ]\n",
      "                \\alpha_w : [ 0.0358    0.0381    0.0631                                        Wing angle of attack\n",
      "                             0.0358    0.0381    0.0631    ]\n",
      "          \\alpha_{max,w} : [ 0.18      0.18      0.18                                          Max angle of attack\n",
      "                             0.18      0.18      0.18      ]\n",
      "                \\eta_{o} : [ 0.126     0.126     0.126                                         Center wing span coefficient\n",
      "                             0.126     0.126     0.126     ]\n",
      "               c_{m_{w}} : [ 1.9       1.9       1.9                                           Wing Pitching Moment Coefficient\n",
      "                             1.9       1.9       1.9       ]\n",
      "               f_{L_{o}} : [ 0.5       0.5       0.5                                           Center wing lift reduction coefficient\n",
      "                             0.5       0.5       0.5       ]\n",
      "               f_{L_{t}} : [ 0.05      0.05      0.05                                          Wing tip lift reduction coefficient\n",
      "                             0.05      0.05      0.05      ]\n",
      "                   p_{o} : [ 2.29e+04  2.28e+04  2.26e+04                        [N/m]         Center section theoretical wing loading\n",
      "                             2.29e+04  2.28e+04  2.26e+04  ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/WingPerformance.2/Relax.1\n",
      "               f_{L_{o}} : [ 1         1         1                                             Center wing lift reduction coefficient\n",
      "                             1         1         1         ]\n",
      "               f_{L_{t}} : [ 1         1         1                                             Wing tip lift reduction coefficient\n",
      "                             1         1         1         ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/FlightState.4\n",
      "                       M : [ 0.651     0.772     0.793                                         Mach Number\n",
      "                             0.651     0.772     0.793     ]\n",
      "                       R : [ 287       287       287                             [J/K/kg]      Air Specific Heat\n",
      "                             287       287       287       ]\n",
      "                       V : [ 411       463       450                             [kt]          Aircraft Flight Speed\n",
      "                             411       463       450       ]\n",
      "                  \\gamma : [ 1.4       1.4       1.4                                           Air Specific Heat Ratio\n",
      "                             1.4       1.4       1.4       ]\n",
      "                       a : [ 325       309       292                             [m/s]         Speed of Sound\n",
      "                             325       309       292       ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/FlightState.4/Altitude.4\n",
      "                       h : [ 3.91e+03  7.82e+03  1.17e+04                        [m]           Segment Altitude [meters]\n",
      "                             3.91e+03  7.82e+03  1.17e+04  ]\n",
      "                     hft : [ 1.28e+04  2.57e+04  3.85e+04                        [ft]          Segment Altitude [feet]\n",
      "                             1.28e+04  2.57e+04  3.85e+04  ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/FlightState.4/Atmosphere.4\n",
      "                     C_1 : [ 1.46e-06  1.46e-06  1.46e-06                        [kg/K⁰.⁵/m/s] Sutherland coefficient\n",
      "                             1.46e-06  1.46e-06  1.46e-06  ]\n",
      "                 L_{atm} : [ 0.0065    0.0065    0.0065                          [K/m]         Temperature lapse rate\n",
      "                             0.0065    0.0065    0.0065    ]\n",
      "                 M_{atm} : [ 0.029     0.029     0.029                           [kg/mol]      Molar mass of dry air\n",
      "                             0.029     0.029     0.029     ]\n",
      "                 P_{atm} : [ 6.24e+04  3.65e+04  2.01e+04                        [Pa]          air pressure\n",
      "                             6.24e+04  3.65e+04  2.01e+04  ]\n",
      "                 R_{atm} : [ 8.31      8.31      8.31                            [J/K/mol]     air specific heating value\n",
      "                             8.31      8.31      8.31      ]\n",
      "                     T_s : [ 110       110       110                             [K]           Sutherland Temperature\n",
      "                             110       110       110       ]\n",
      "                 T_{atm} : [ 263       237       212                             [K]           air temperature\n",
      "                             263       237       212       ]\n",
      "                  T_{sl} : [ 288       288       288                             [K]           Temperature at sea level\n",
      "                             288       288       288       ]\n",
      "                     \\mu : [ 3.16e-05  2.71e-05  2.29e-05                        [kg/m/s]      Dynamic viscosity\n",
      "                             3.16e-05  2.71e-05  2.29e-05  ]\n",
      "                    \\rho : [ 0.827     0.536     0.331                           [kg/m³]       Density of air\n",
      "                             0.827     0.536     0.331     ]\n",
      "                  p_{sl} : [ 1.01e+05  1.01e+05  1.01e+05                        [Pa]          Pressure at sea level\n",
      "                             1.01e+05  1.01e+05  1.01e+05  ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/FlightState.4/Atmosphere.4/Relax.1\n",
      "                     C_1 : [ 1         1         1                                             Sutherland coefficient\n",
      "                             1         1         1         ]\n",
      "                 L_{atm} : [ 1         1         1                                             Temperature lapse rate\n",
      "                             1         1         1         ]\n",
      "                 M_{atm} : [ 1         1         1                                             Molar mass of dry air\n",
      "                             1         1         1         ]\n",
      "                 R_{atm} : [ 1         1         1                                             air specific heating value\n",
      "                             1         1         1         ]\n",
      "                     T_s : [ 1         1         1                                             Sutherland Temperature\n",
      "                             1         1         1         ]\n",
      "                  T_{sl} : [ 1         1         1                                             Temperature at sea level\n",
      "                             1         1         1         ]\n",
      "                  p_{sl} : [ 1         1         1                                             Pressure at sea level\n",
      "                             1         1         1         ]\n",
      "\n",
      "                         | Mission.1/ClimbSegment.1/FlightState.4/Relax.1\n",
      "                       R : [ 1         1         1                                             Air Specific Heat\n",
      "                             1         1         1         ]\n",
      "                  \\gamma : [ 1         1         1                                             Air Specific Heat Ratio\n",
      "                             1         1         1         ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1\n",
      "                      RC : [ 5.1e-12   5.1e-12                                   [ft/min]      Rate of Climb/Descent\n",
      "                             12.4      12.4      ]\n",
      "              R_{cruise} : [ 1.44e+03  1.44e+03                                  [nmi]         Cruise Segment Range\n",
      "                             1.44e+03  1.44e+03  ]\n",
      "                  \\theta : [ 1.23e-16  1.23e-16                                                Climb Angle\n",
      "                             0.000304  0.000304  ]\n",
      "                    dhft : [ 1.08e-09  1.08e-09                                  [ft]          Change in Altitude Per Climb Segment [feet]\n",
      "                             2.66e+03  2.66e+03  ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3\n",
      "                     C_D : [ 0.0253    0.0253                                                  Total Aircraft Drag Coefficient\n",
      "                             0.0268    0.0268    ]\n",
      "         C_{d_{nacelle}} : [ 0.000838  0.000838                                                Nacelle Drag Coeffecient\n",
      "                             0.000838  0.000838  ]\n",
      "         C_{f_{nacelle}} : [ 0.0131    0.0131                                                  Nacelle Drag Coefficient\n",
      "                             0.0133    0.0133    ]\n",
      "                       D : [ 2.55e+04  2.55e+04                                  [N]           Total Aircraft Drag\n",
      "                             2.37e+04  2.37e+04  ]\n",
      "             D_{nacelle} : [ 845       845                                       [N]           Drag On One Nacelle\n",
      "                             741       741       ]\n",
      "                F_{fuel} : [ 0.448     0.448                                                   Percent Fuel Remaining (end of segment)\n",
      "                             1e-07     1e-07     ]\n",
      "                     L/D : [ 24.2      24.2                                                    Lift-to-Drag Ratio\n",
      "                             24.4      24.4      ]\n",
      "               L_{total} : [ 6.19e+05  6.19e+05                                  [N]           Total lift\n",
      "                             5.79e+05  5.79e+05  ]\n",
      "               P_{cabin} : [ 7.5e+04   7.5e+04                                   [Pa]          Cabin Air Pressure\n",
      "                             7.5e+04   7.5e+04   ]\n",
      "         R_{e_{nacelle}} : [ 4.48e+06  4.48e+06                                                Nacelle Reynolds Number\n",
      "                             4.13e+06  4.13e+06  ]\n",
      "                      SM : [ 0.109     0.109                                                   Stability Margin of Aircraft\n",
      "                             0.115     0.115     ]\n",
      "               T_{cabin} : [ 297       297                                       [K]           Cabin Air Temperature\n",
      "                             297       297       ]\n",
      "                     V_2 : [ 210       210                                       [m/s]         Interior Nacelle Flow Velcoity\n",
      "                             207       207       ]\n",
      "       V_{nacelle_ratio} : [ 0.85      0.85                                                    Vnle/Vinf\n",
      "                             0.85      0.85      ]\n",
      "             V_{nacelle} : [ 194       194                                       [m/s]         Incoming Nacelle Flow Velocity\n",
      "                             192       192       ]\n",
      "               V_{stall} : [ 120       120                                       [kt]          Aircraft Stall Speed\n",
      "                             120       120       ]\n",
      "          W_{Load_{max}} : [ 6.66e+03  6.66e+03                                  [N/m²]        Max Wing Loading\n",
      "                             6.66e+03  6.66e+03  ]\n",
      "                W_{Load} : [ 3.96e+03  3.96e+03                                  [N/m²]        Wing Loading\n",
      "                             3.7e+03   3.7e+03   ]\n",
      "                 W_{avg} : [ 1.39e+05  1.39e+05                                  [lbf]         Geometric Average of Segment Start and End Weight\n",
      "                             1.3e+05   1.3e+05   ]\n",
      "                W_{buoy} : [ 786       786                                       [lbf]         Buoyancy Weight\n",
      "                             786       786       ]\n",
      "                W_{burn} : [ 9.39e+03  9.39e+03                                  [lbf]         Segment Fuel Burn Weight\n",
      "                             8.77e+03  8.77e+03  ]\n",
      "                 W_{end} : [ 1.33e+05  1.33e+05                                  [lbf]         Segment End Weight\n",
      "                             1.25e+05  1.25e+05  ]\n",
      "               W_{start} : [ 1.43e+05  1.43e+05                                  [lbf]         Segment Start Weight\n",
      "                             1.33e+05  1.33e+05  ]\n",
      "            \\rho_{cabin} : [ 0.88      0.88                                      [kg/m³]       Cabin Air Density\n",
      "                             0.88      0.88      ]\n",
      "           r_{v_{nsurf}} : [ 0.888     0.888                                                   Intermediate Nacelle Drag Parameter\n",
      "                             0.888     0.888     ]\n",
      "                     thr : [ 3.53      3.53                                      [hr]          Segment Flight Time in Hours\n",
      "                             3.57      3.57      ]\n",
      "                    tmin : [ 212       212                                       [min]         Segment Flight Time in Minutes\n",
      "                             214       214       ]\n",
      "                  x_{AC} : [ 22        22                                        [m]           Aerodynamic Center of Aircraft\n",
      "                             21.8      21.8      ]\n",
      "                  x_{CG} : [ 20.4      20.4                                      [m]           Center of Gravity of Aircraft\n",
      "                             19.9      19.9      ]\n",
      "                  x_{NP} : [ 1.57      1.57                                      [m]           Neutral Point of Aircraft\n",
      "                             1.57      1.57      ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/FuselagePerformance.3\n",
      "            C_{D_{fuse}} : [ 0.0181    0.0181                                                  Fuselage Drag Coefficient\n",
      "                             0.0181    0.0181    ]\n",
      "                D_{fuse} : [ 7.25e+03  7.25e+03                                  [N]           Fuselage Drag\n",
      "                             6.36e+03  6.36e+03  ]\n",
      "                L_{fuse} : [ 1.01e+05  1.01e+05                                  [N]           Fuselage Lift\n",
      "                             9.45e+04  9.45e+04  ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/HorizontalTailPerformance.3\n",
      "            C_{D_{0,ht}} : [ 0.0024    0.0024                                                  Horizontal tail parasitic drag coefficient\n",
      "                             0.00237   0.00237   ]\n",
      "              C_{D_{ht}} : [ 0.00241   0.00241                                                 Horizontal tail drag coefficient\n",
      "                             0.00238   0.00238   ]\n",
      "     C_{L_{\\alpha,ht_0}} : [ 6.28      6.28                                                    Isolated lift curve slope (htail)\n",
      "                             6.28      6.28      ]\n",
      "       C_{L_{\\alpha,ht}} : [ 0.0743    0.0743                                                  Lift curve slope (htail)\n",
      "                             0.0743    0.0743    ]\n",
      "              C_{L_{ht}} : [ 0.01      0.01                                                    Lift coefficient (htail)\n",
      "                             0.01      0.01      ]\n",
      "                  D_{ht} : [ 538       538                                       [N]           Horizontal tail drag\n",
      "                             466       466       ]\n",
      "                  L_{ht} : [ 2.23e+03  2.23e+03                                  [N]           Horizontal tail downforce\n",
      "                             1.96e+03  1.96e+03  ]\n",
      "                Re_{c_h} : [ 8e+06     8e+06                                                   Cruise Reynolds number (Horizontal tail)\n",
      "                             7.38e+06  7.38e+06  ]\n",
      "             \\alpha_{ht} : [ 0.135     0.135                                                   Horizontal tail angle of attack\n",
      "                             0.135     0.135     ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/Relax.1\n",
      "               V_{stall} : [ 1         1                                                       Aircraft Stall Speed\n",
      "                             1         1         ]\n",
      "          W_{Load_{max}} : [ 1         1                                                       Max Wing Loading\n",
      "                             1         1         ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/VerticalTailPerformance.3\n",
      "             C_{D_{vis}} : [ 0.014     0.014                                                   Viscous drag coefficient\n",
      "                             0.0138    0.0138    ]\n",
      "                  D_{vt} : [ 672       672                                       [N]           Vertical tail viscous drag, cruise\n",
      "                             581       581       ]\n",
      "                 Re_{vt} : [ 5.75e+06  5.75e+06                                                Vertical tail reynolds number, cruise\n",
      "                             5.3e+06   5.3e+06   ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/WingPerformance.3\n",
      "             C_{D_{i_w}} : [ 0.00793   0.00793                                                 Wing induced drag coefficient\n",
      "                             0.009     0.009     ]\n",
      "             C_{D_{p_w}} : [ 0.00703   0.00703                                                 Wing parasitic drag coefficient\n",
      "                             0.00748   0.00748   ]\n",
      "        C_{L_{\\alpha,w}} : [ 6.74      6.74                                                    Lift curve slope, wing\n",
      "                             6.74      6.74      ]\n",
      "                   C_{L} : [ 0.542     0.542                                                   Lift coefficient, wing\n",
      "                             0.578     0.578     ]\n",
      "                 C_{d_w} : [ 0.015     0.015                                                   Drag coefficient, wing\n",
      "                             0.0165    0.0165    ]\n",
      "                D_{wing} : [ 1.51e+04  1.51e+04                                  [N]           Wing drag\n",
      "                             1.46e+04  1.46e+04  ]\n",
      "                     L_w : [ 5.18e+05  5.18e+05                                  [N]           Wing lift\n",
      "                             4.84e+05  4.84e+05  ]\n",
      "                    Re_w : [ 1.19e+07  1.19e+07                                                Reynolds number (wing)\n",
      "                             1.1e+07   1.1e+07   ]\n",
      "            \\Delta L_{o} : [ 2.84e+04  2.84e+04                                  [N]           Center wing lift loss\n",
      "                             2.65e+04  2.65e+04  ]\n",
      "            \\Delta L_{t} : [ 141       141                                       [N]           Wing tip lift loss\n",
      "                             132       132       ]\n",
      "                \\alpha_w : [ 0.0805    0.0805                                                  Wing angle of attack\n",
      "                             0.0857    0.0857    ]\n",
      "          \\alpha_{max,w} : [ 0.1       0.1                                                     Max angle of attack\n",
      "                             0.1       0.1       ]\n",
      "                \\eta_{o} : [ 0.126     0.126                                                   Center wing span coefficient\n",
      "                             0.126     0.126     ]\n",
      "               c_{m_{w}} : [ 1.9       1.9                                                     Wing Pitching Moment Coefficient\n",
      "                             1.9       1.9       ]\n",
      "               f_{L_{o}} : [ 0.5       0.5                                                     Center wing lift reduction coefficient\n",
      "                             0.5       0.5       ]\n",
      "               f_{L_{t}} : [ 0.05      0.05                                                    Wing tip lift reduction coefficient\n",
      "                             0.05      0.05      ]\n",
      "                   p_{o} : [ 2.17e+04  2.17e+04                                  [N/m]         Center section theoretical wing loading\n",
      "                             2.03e+04  2.03e+04  ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/WingPerformance.3/Relax.1\n",
      "               f_{L_{o}} : [ 1         1                                                       Center wing lift reduction coefficient\n",
      "                             1         1         ]\n",
      "               f_{L_{t}} : [ 1         1                                                       Wing tip lift reduction coefficient\n",
      "                             1         1         ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/FlightState.5\n",
      "                       M : [ 0.72      0.72                                                    Mach Number\n",
      "                             0.72      0.72      ]\n",
      "                       R : [ 287       287                                       [J/K/kg]      Air Specific Heat\n",
      "                             287       287       ]\n",
      "                       V : [ 408       408                                       [kt]          Aircraft Flight Speed\n",
      "                             403       403       ]\n",
      "                  \\gamma : [ 1.4       1.4                                                     Air Specific Heat Ratio\n",
      "                             1.4       1.4       ]\n",
      "                       a : [ 292       292                                       [m/s]         Speed of Sound\n",
      "                             288       288       ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/FlightState.5/Altitude.5\n",
      "                       h : [ 1.17e+04  1.17e+04                                  [m]           Segment Altitude [meters]\n",
      "                             1.25e+04  1.25e+04  ]\n",
      "                     hft : [ 3.85e+04  3.85e+04                                  [ft]          Segment Altitude [feet]\n",
      "                             4.11e+04  4.11e+04  ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/FlightState.5/Atmosphere.5\n",
      "                     C_1 : [ 1.46e-06  1.46e-06                                  [kg/K⁰.⁵/m/s] Sutherland coefficient\n",
      "                             1.46e-06  1.46e-06  ]\n",
      "                 L_{atm} : [ 0.0065    0.0065                                    [K/m]         Temperature lapse rate\n",
      "                             0.0065    0.0065    ]\n",
      "                 M_{atm} : [ 0.029     0.029                                     [kg/mol]      Molar mass of dry air\n",
      "                             0.029     0.029     ]\n",
      "                 P_{atm} : [ 2.01e+04  2.01e+04                                  [Pa]          air pressure\n",
      "                             1.77e+04  1.77e+04  ]\n",
      "                 R_{atm} : [ 8.31      8.31                                      [J/K/mol]     air specific heating value\n",
      "                             8.31      8.31      ]\n",
      "                     T_s : [ 110       110                                       [K]           Sutherland Temperature\n",
      "                             110       110       ]\n",
      "                 T_{atm} : [ 212       212                                       [K]           air temperature\n",
      "                             207       207       ]\n",
      "                  T_{sl} : [ 288       288                                       [K]           Temperature at sea level\n",
      "                             288       288       ]\n",
      "                     \\mu : [ 2.29e-05  2.29e-05                                  [kg/m/s]      Dynamic viscosity\n",
      "                             2.21e-05  2.21e-05  ]\n",
      "                    \\rho : [ 0.331     0.331                                     [kg/m³]       Density of air\n",
      "                             0.298     0.298     ]\n",
      "                  p_{sl} : [ 1.01e+05  1.01e+05                                  [Pa]          Pressure at sea level\n",
      "                             1.01e+05  1.01e+05  ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/FlightState.5/Atmosphere.5/Relax.1\n",
      "                     C_1 : [ 1         1                                                       Sutherland coefficient\n",
      "                             1         1         ]\n",
      "                 L_{atm} : [ 1         1                                                       Temperature lapse rate\n",
      "                             1         1         ]\n",
      "                 M_{atm} : [ 1         1                                                       Molar mass of dry air\n",
      "                             1         1         ]\n",
      "                 R_{atm} : [ 1         1                                                       air specific heating value\n",
      "                             1         1         ]\n",
      "                     T_s : [ 1         1                                                       Sutherland Temperature\n",
      "                             1         1         ]\n",
      "                  T_{sl} : [ 1         1                                                       Temperature at sea level\n",
      "                             1         1         ]\n",
      "                  p_{sl} : [ 1         1                                                       Pressure at sea level\n",
      "                             1         1         ]\n",
      "\n",
      "                         | Mission.1/CruiseSegment.1/FlightState.5/Relax.1\n",
      "                       R : [ 1         1                                                       Air Specific Heat\n",
      "                             1         1         ]\n",
      "                  \\gamma : [ 1         1                                                       Air Specific Heat Ratio\n",
      "                             1         1         ]\n",
      "\n",
      "                         | Mission.1/FlightState.3\n",
      "                       M : [ 0.651     0.772     0.793     0.72      0.72                      Mach Number\n",
      "                             0.651     0.772     0.793     0.72      0.72      ]\n",
      "                       R : [ 287       287       287       287       287         [J/K/kg]      Air Specific Heat\n",
      "                             287       287       287       287       287       ]\n",
      "                       V : [ 411       463       450       408       403         [kt]          Aircraft Flight Speed\n",
      "                             411       463       450       408       403       ]\n",
      "                  \\gamma : [ 1.4       1.4       1.4       1.4       1.4                       Air Specific Heat Ratio\n",
      "                             1.4       1.4       1.4       1.4       1.4       ]\n",
      "                       a : [ 325       309       292       292       288         [m/s]         Speed of Sound\n",
      "                             325       309       292       292       288       ]\n",
      "\n",
      "                         | Mission.1/FlightState.3/Altitude.3\n",
      "                       h : [ 3.91e+03  7.82e+03  1.17e+04  1.17e+04  1.25e+04    [m]           Segment Altitude [meters]\n",
      "                             3.91e+03  7.82e+03  1.17e+04  1.17e+04  1.25e+04  ]\n",
      "                     hft : [ 1.28e+04  2.57e+04  3.85e+04  3.85e+04  4.11e+04    [ft]          Segment Altitude [feet]\n",
      "                             1.28e+04  2.57e+04  3.85e+04  3.85e+04  4.11e+04  ]\n",
      "\n",
      "                         | Mission.1/FlightState.3/Atmosphere.3\n",
      "                     C_1 : [ 1.46e-06  1.46e-06  1.46e-06  1.46e-06  1.46e-06    [kg/K⁰.⁵/m/s] Sutherland coefficient\n",
      "                             1.46e-06  1.46e-06  1.46e-06  1.46e-06  1.46e-06  ]\n",
      "                 L_{atm} : [ 0.0065    0.0065    0.0065    0.0065    0.0065      [K/m]         Temperature lapse rate\n",
      "                             0.0065    0.0065    0.0065    0.0065    0.0065    ]\n",
      "                 M_{atm} : [ 0.029     0.029     0.029     0.029     0.029       [kg/mol]      Molar mass of dry air\n",
      "                             0.029     0.029     0.029     0.029     0.029     ]\n",
      "                 P_{atm} : [ 6.24e+04  3.65e+04  2.01e+04  2.01e+04  1.77e+04    [Pa]          air pressure\n",
      "                             6.24e+04  3.65e+04  2.01e+04  2.01e+04  1.77e+04  ]\n",
      "                 R_{atm} : [ 8.31      8.31      8.31      8.31      8.31        [J/K/mol]     air specific heating value\n",
      "                             8.31      8.31      8.31      8.31      8.31      ]\n",
      "                     T_s : [ 110       110       110       110       110         [K]           Sutherland Temperature\n",
      "                             110       110       110       110       110       ]\n",
      "                 T_{atm} : [ 263       237       212       212       207         [K]           air temperature\n",
      "                             263       237       212       212       207       ]\n",
      "                  T_{sl} : [ 288       288       288       288       288         [K]           Temperature at sea level\n",
      "                             288       288       288       288       288       ]\n",
      "                     \\mu : [ 3.16e-05  2.71e-05  2.29e-05  2.29e-05  2.21e-05    [kg/m/s]      Dynamic viscosity\n",
      "                             3.16e-05  2.71e-05  2.29e-05  2.29e-05  2.21e-05  ]\n",
      "                    \\rho : [ 0.827     0.536     0.331     0.331     0.298       [kg/m³]       Density of air\n",
      "                             0.827     0.536     0.331     0.331     0.298     ]\n",
      "                  p_{sl} : [ 1.01e+05  1.01e+05  1.01e+05  1.01e+05  1.01e+05    [Pa]          Pressure at sea level\n",
      "                             1.01e+05  1.01e+05  1.01e+05  1.01e+05  1.01e+05  ]\n",
      "\n",
      "                         | Mission.1/FlightState.3/Atmosphere.3/Relax.1\n",
      "                     C_1 : [ 1         1         1         1         1                         Sutherland coefficient\n",
      "                             1         1         1         1         1         ]\n",
      "                 L_{atm} : [ 1         1         1         1         1                         Temperature lapse rate\n",
      "                             1         1         1         1         1         ]\n",
      "                 M_{atm} : [ 1         1         1         1         1                         Molar mass of dry air\n",
      "                             1         1         1         1         1         ]\n",
      "                 R_{atm} : [ 1         1         1         1         1                         air specific heating value\n",
      "                             1         1         1         1         1         ]\n",
      "                     T_s : [ 1         1         1         1         1                         Sutherland Temperature\n",
      "                             1         1         1         1         1         ]\n",
      "                  T_{sl} : [ 1         1         1         1         1                         Temperature at sea level\n",
      "                             1         1         1         1         1         ]\n",
      "                  p_{sl} : [ 1         1         1         1         1                         Pressure at sea level\n",
      "                             1         1         1         1         1         ]\n",
      "\n",
      "                         | Mission.1/FlightState.3/Relax.1\n",
      "                       R : [ 1         1         1         1         1                         Air Specific Heat\n",
      "                             1         1         1         1         1         ]\n",
      "                  \\gamma : [ 1         1         1         1         1                         Air Specific Heat Ratio\n",
      "                             1         1         1         1         1         ]\n",
      "\n",
      "                         | Mission.1/Relax.1\n",
      "              Fsafetyfac : 1                                                                   Safety factor on inital climb thrust\n",
      "            MaxClimbTime : 1                                                                   Total Time in Climb\n",
      "            MinCruiseAlt : 1                                                                   Minimum Cruise Altitude\n",
      "               OPR_{max} : 1                                                                   Maximum Overall Pressure Ratio\n",
      "                 R_{req} : [ 1         1        ]                                              Required Cruise Range\n",
      "\n",
      "Constants\n",
      "---------\n",
      "                               | Mission.1/Aircraft.1/Engine.1/Combustor.1/Relax.1\n",
      "            C_{p_{c}}_{before} : 1258                                                  [J/K/kg]      Cp Value for Fuel/Air Mix in Combustor\n",
      "          C_{p_{fuel}_{before} : 2010                                                  [J/K/kg]      Specific Heat Capacity of Kerosene (~Jet Fuel)\n",
      "              T_{t_f}_{before} : 435                                                   [K]           Incoming Fuel Total Temperature\n",
      "             \\alpha_c_{before} : 0.16                                                                Total Cooling Flow Bypass Ratio\n",
      "             \\eta_{B}_{before} : 0.985                                                               Burner Efficiency\n",
      "              \\pi_{b}_{before} : 0.94                                                                Burner Pressure Ratio\n",
      "                h_{f}_{before} : 43                                                    [MJ/kg]       Heat of Combustion of Jet Fuel\n",
      "            hold_{4a}_{before} : 1.006                                                               1+(gamma-1)/2 * M_4a**2\n",
      "               r_{uc}_{before} : 0.01                                                                User Specified Cooling Flow Velocity Ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/Compressor.1/Relax.1\n",
      "             C_{p_{1}_{before} : 1008                                                  [J/K/kg]      Cp Value for Air at 350K\n",
      "             C_{p_{2}_{before} : 1099                                                  [J/K/kg]      Cp Value for Air at 800K\n",
      "           C_{p_{air}_{before} : 1003                                                  [J/K/kg]      Cp Value for Air at 250K\n",
      "         \\gamma_{air}_{before} : 1.4                                                                 Specific Heat Ratio for Ambient Air\n",
      "              \\pi_{d}_{before} : 0.995                                                               Diffuser Pressure Ratio\n",
      "             \\pi_{fn}_{before} : 0.985                                                               Fan Duct Pressure Loss Ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/EngineConstants.1\n",
      "                   M_{takeoff} : 0.9556                                                              1 Minus Percent mass flow loss for de-ice, pressurization, etc.\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/EngineConstants.1/Relax.1\n",
      "              P_{ref}_{before} : 101.3                                                 [kPa]         Reference Stagnation Pressure\n",
      "                    R_{before} : 287                                                   [J/K/kg]      R\n",
      "              T_{ref}_{before} : 288.1                                                 [K]           Reference Stagnation Temperature\n",
      "          f_{BLI_{P}}_{before} : 0.9627                                                              BLI Stagnation Pressure Loss Ratio\n",
      "          f_{BLI_{V}}_{before} : 0.9273                                                              BLI Velocity Loss Ratio\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Gravitational Acceleration\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/SizingPerformance.1/Relax.1\n",
      "                 dum2_{before} : [ 1         1         1         1         1           [m/s]\n",
      "                                   1         1         1         1         1         ]\n",
      "                  dum_{before} : [ 781       781       781       781       781         [J/K/kg]\n",
      "                                   781       781       781       781       781       ]\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/FanMap.1/Relax.1\n",
      "            \\pi_{f_D}_{before} : 1.605                                                               On-Design Pressure Ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/Relax.1\n",
      "        HTR_{f_{SUB}}_{before} : 0.91                                                                1 - HTRf^2\n",
      "      HTR_{lpc_{SUB}}_{before} : 0.64                                                                1 - HTRlpc^2\n",
      "    T_{t_{4.1_{max}}}_{before} : 1567                                                  [K]           Max turbine inlet temperature\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/Sizing.1/Relax.1\n",
      "                G_{f}_{before} : 1                                                                   Gear Ratio Between Fan and LPC\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/Thrust.1/Relax.1\n",
      "           C_{p_{fex}_{before} : 1005                                                  [J/K/kg]      Cp Value for Air at 300K\n",
      "           C_{p_{tex}_{before} : 1029                                                  [J/K/kg]      Cp Value for Combustion Products at Core Exhaust\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Engine.1/Turbine.1/Relax.1\n",
      "           C_{p_{t1}}_{before} : 1236                                                  [J/K/kg]      Cp Value for Combustion Products in HP Turbine\n",
      "           C_{p_{t2}}_{before} : 1200                                                  [J/K/kg]      Cp Value for Combustion Products in LP Turbine\n",
      "       \\eta_{HPshaft}_{before} : 0.978                                                               Power Transmission Efficiency of High Pressure Shaft, Smears in Losses for Electrical Power\n",
      "       \\eta_{LPshaft}_{before} : 0.99                                                                Power Transmission Efficiency of Low Pressure Shaft, Smeras in Losses for Electrical Power\n",
      "             \\pi_{tn}_{before} : 0.995                                                               Turbine Nozzle Pressure Ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Fuselage.1/Relax.1\n",
      "             C_{fuse}_{before} : 1                                                                   Fuselage Weight Margin and Sensitivity\n",
      "             N_{land}_{before} : 6                                                                   Emergency landing load factor\n",
      "                  SPR_{before} : 8                                                                   Number of seats per row\n",
      "          W''_{floor}_{before} : 60                                                    [N/m²]        Floor weight/area density\n",
      "          W''_{insul}_{before} : 22                                                    [N/m²]        Weight/area density of insulation material\n",
      "            W'_{seat}_{before} : 1                                                     [N]           Weight per seat\n",
      "          W'_{window}_{before} : 435                                                   [N/m]         Weight/length density of windows\n",
      "W_{avg. pass_{total}}_{before} : 215                                                   [lbf]         Average passenger weight including payload\n",
      "        W_{avg. pass}_{before} : 180                                                   [lbf]         Average passenger weight\n",
      "            W_{cargo}_{before} : 0.02248                                               [lbf]         Cargo weight\n",
      "         W_{carry on}_{before} : 15                                                    [lbf]         Ave. carry-on weight\n",
      "          W_{checked}_{before} : 40                                                    [lbf]         Ave. checked bag weight\n",
      "              W_{fix}_{before} : 3000                                                  [lbf]         Fixed weights (pilots, cockpit seats, navcom)\n",
      "      \\Delta P_{over}_{before} : 8.382                                                 [psi]         Cabin overpressure\n",
      "       \\lambda_{cone}_{before} : 0.3                                                                 Tailcone radius taper ratio\n",
      "          \\rho_{bend}_{before} : 2700                                                  [kg/m³]       Stringer density\n",
      "         \\rho_{cargo}_{before} : 150                                                   [kg/m³]       Cargo density\n",
      "          \\rho_{cone}_{before} : 2700                                                  [kg/m³]       Cone material density\n",
      "         \\rho_{floor}_{before} : 2700                                                  [kg/m³]       Floor material density\n",
      "          \\rho_{lugg}_{before} : 100                                                   [kg/m³]       Luggage density\n",
      "          \\rho_{skin}_{before} : 2700                                                  [kg/m³]       Skin density\n",
      "        \\sigma_{bend}_{before} : 2.069e+08                                             [N/m²]        Bending material stress\n",
      "       \\sigma_{floor}_{before} : 2.069e+08                                             [N/m²]        Max allowable floor stress\n",
      "        \\sigma_{skin}_{before} : 1.034e+08                                             [N/m²]        Max allowable skin stress\n",
      "         \\tau_{floor}_{before} : 2.069e+08                                             [N/m²]        Max allowable shear web stress\n",
      "              f_{apu}_{before} : 0.035                                                               APU weight as fraction of payload weight\n",
      "             f_{fadd}_{before} : 0.2                                                                 Fractional added weight of local reinforcements\n",
      "            f_{frame}_{before} : 0.25                                                                Fractional frame weight\n",
      "           f_{lugg,1}_{before} : 0.4                                                                 Proportion of passengers with one suitcase\n",
      "           f_{lugg,2}_{before} : 0.1                                                                 Proportion of passengers with two suitcases\n",
      "             f_{padd}_{before} : 0.35                                                                Other misc weight as fraction of payload weight\n",
      "             f_{seat}_{before} : 0.1                                                                 Fractional seat weight\n",
      "           f_{string}_{before} : 0.35                                                                Fractional stringer weight\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Acceleration due to gravity\n",
      "            h_{floor}_{before} : 0.13                                                  [m]           Floor beam height\n",
      "             l_{nose}_{before} : 8.839                                                 [m]           Nose length\n",
      "                  p_s_{before} : 81                                                    [cm]          Seat pitch\n",
      "     p_{\\lambda_{vt}}_{before} : 1.6                                                                 1 + 2*Tail taper ratio\n",
      "                  r_E_{before} : 1                                                                   Ratio of stringer/skin moduli\n",
      "              r_{M_h}_{before} : 0.4                                                                 Horizontal inertial relief factor\n",
      "              r_{M_v}_{before} : 0.7                                                                 Vertical inertial relief factor\n",
      "              r_{w/c}_{before} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "            w_{aisle}_{before} : 0.51                                                  [m]           Aisle width\n",
      "               w_{db}_{before} : 0.93                                                  [m]           DB added half-width\n",
      "             w_{seat}_{before} : 0.5                                                   [m]           Seat width\n",
      "              w_{sys}_{before} : 0.1                                                   [m]           Width between cabin and skin for systems\n",
      "             n_{pass}_{before} : [ 180       180      ]                                              Number of passengers\n",
      "\n",
      "                               | Mission.1/Aircraft.1/HorizontalTail.1/HorizontalTailNoStruct.1/Relax.1\n",
      "       C_{L_{ht,fCG}}_{before} : 0.85                                                                HT CL During Max Forward CG\n",
      "       C_{L_{ht,max}}_{before} : 2                                                                   Max lift coefficient\n",
      "      \\alpha_{ht,max}_{before} : 2.5                                                                 Max angle of attack, htail\n",
      "            \\eta_{ht}_{before} : 1                                                                   Tail efficiency\n",
      "         \\lambda_{ht}_{before} : 0.3                                                                 Horizontal tail taper ratio\n",
      "   \\tan(\\Lambda_{ht})_{before} : 0.1405                                                              tangent of horizontal tail sweep\n",
      "\n",
      "                               | Mission.1/Aircraft.1/HorizontalTail.1/Relax.1\n",
      "               C_{ht}_{before} : 1                                                                   HT Weight Margin and Sensitivity Factor\n",
      " \\cos(\\Lambda_{ht})^3_{before} : 0.9711                                                              Cosine of tail sweep cubed\n",
      "           c_{d_{fh}}_{before} : 0.006                                                               VT friction drag coefficient\n",
      "           c_{d_{ph}}_{before} : 0.0035                                                              VT pressure drag coefficient\n",
      "               f_{ht}_{before} : 0.3                                                                 Rudder etc. fractional weight\n",
      "\n",
      "                               | Mission.1/Aircraft.1/HorizontalTail.1/WingBox.5/Relax.1\n",
      "           \\rho_{cap}_{before} : 2700                                                  [kg/m³]       Density of spar cap material\n",
      "           \\rho_{web}_{before} : 2700                                                  [kg/m³]       Density of shear web material\n",
      "   \\sigma_{max,shear}_{before} : 1.67e+08                                              [Pa]          Allowable shear stress\n",
      "         \\sigma_{max}_{before} : 2.5e+08                                               [Pa]          Allowable tensile stress\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                  r_h_{before} : 0.75                                                                Fractional wing thickness at spar web\n",
      "              r_{w/c}_{before} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "                taper_{before} : 0.3                                                                 Taper ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/LandingGear.1/Relax.1\n",
      "               C_{lg}_{before} : 1                                                                   Landing Gear Weight Margin/Sens Factor\n",
      "                    E_{before} : 205                                                   [GPa]         Modulus of elasticity, 4340 steel\n",
      "                    K_{before} : 2                                                                   Column effective length factor\n",
      "                  N_s_{before} : 2                                                                   Factor of safety\n",
      "               \\eta_s_{before} : 0.8                                                                 Shock absorber efficiency\n",
      "         \\lambda_{LG}_{before} : 2.5                                                                 Ratio of max to static load\n",
      "            \\rho_{st}_{before} : 7850                                                  [kg/m³]       Density of 4340 Steel\n",
      "         \\sigma_{y_c}_{before} : 4.7e+08                                               [Pa]          Compressive yield strength 4340 steel\n",
      "         \\tan(\\gamma)_{before} : 0.08749                                                             Dihedral angle\n",
      "     \\tan(\\phi_{min})_{before} : 0.2679                                                              Lower bound on phi\n",
      "     \\tan(\\psi_{max})_{before} : 1.963                                                               Upper bound on psi\n",
      "   \\tan(\\theta_{max})_{before} : 0.2679                                                              Max rotation angle\n",
      "            f_{add,m}_{before} : 1.5                                                                 Proportional added weight, main\n",
      "            f_{add,n}_{before} : 1.5                                                                 Proportional added weight, nose\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "             h_{hold}_{before} : 1                                                     [m]           Hold height\n",
      "               n_{mg}_{before} : 2                                                                   Number of main gear struts\n",
      "              n_{wps}_{before} : 2                                                                   Number of wheels per strut\n",
      "             p_{oleo}_{before} : 1800                                                  [lbf/in²]     Oleo pressure\n",
      "          t_{nacelle}_{before} : 0.15                                                  [m]           Nacelle thickness\n",
      "              w_{ult}_{before} : 10                                                    [ft/s]        Ultimate velocity of descent\n",
      "               z_{CG}_{before} : 2                                                     [m]           CG height relative to bottom of fuselage\n",
      "             z_{wing}_{before} : 0.5                                                   [m]           Height of wing relative to base of fuselage\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Relax.1\n",
      "    BLI_{wakebenefit}_{before} : 0.02                                                                Wake Drag Reduction from BLI Wake Ingestion\n",
      "           C_{engsys}_{before} : 1                                                                   Engine System Weight Margin/Sens Factor\n",
      "           D_{reduct}_{before} : 0.9842                                                              BLI Drag Reduction Factor\n",
      "     D_{wakefraction}_{before} : 0.33                                                                Percent of Total Drag From Wake Dissipation\n",
      "              M_{min}_{before} : 0.72                                                                Minimum Cruise Mach Number\n",
      "             SM_{min}_{before} : 0.05                                                                Minimum Static Margin\n",
      "               V_{mn}_{before} : 133.8                                                 [m/s]         Maneuvering speed\n",
      "               V_{ne}_{before} : 143.9                                                 [m/s]         Never-exceed speed\n",
      "        \\Delta x_{CG}_{before} : 1.829                                                 [m]           Max CG Travel Range\n",
      "           \\rho_{T/O}_{before} : 1.225                                                 [kg/m³]       Air density at takeoff\n",
      "   f_{L_{total/wing}}_{before} : 1.195                                                               Total lift as a percentage of wing lift\n",
      "             f_{eadd}_{before} : 0.1                                                                 Additional Engine Weight Fraction\n",
      "       f_{fuel_{res}}_{before} : 0.2                                                                 Fuel Reserve Fraction\n",
      "           f_{hpesys}_{before} : 0.01                                                                Power Systems Weight Fraction\n",
      "            f_{pylon}_{before} : 0.05                                                                Pylong Weight Fraction\n",
      "         f_{wingfuel}_{before} : 1                                                                   Fraction of fuel stored in wing tanks\n",
      "            n_{aisle}_{before} : 2                                                                   Number of Aisles\n",
      "              n_{eng}_{before} : 2                                                                   Number of Engines\n",
      "               n_{vt}_{before} : 2                                                                   Number of Vertical Tails\n",
      "      r_{S_{nacelle}}_{before} : 6                                                                   Nacelle and Pylon Wetted Area\n",
      "      r_{v_{nacelle}}_{before} : 0.925                                                               Incoming Nacelle Velocity Ratio\n",
      "         x_{CG_{min}}_{before} : 17.07                                                 [m]           Maximum Forward CG\n",
      "\n",
      "                               | Mission.1/Aircraft.1/VerticalTail.1/Relax.1\n",
      "               C_{VT}_{before} : 1                                                                   VT Weight Margin and Sensitivity\n",
      "             N_{spar}_{before} : 1                                                                   Number of Spars in Each VT Carrying Stress in 1 in 20 Case\n",
      " \\cos(\\Lambda_{vt})^3_{before} : 0.7444                                                              Cosine of tail sweep cubed\n",
      "           c_{d_{fv}}_{before} : 0.006                                                               VT friction drag coefficient\n",
      "           c_{d_{pv}}_{before} : 0.0035                                                              VT pressure drag coefficient\n",
      "               f_{VT}_{before} : 0.4                                                                 VT Fractional Weight\n",
      "\n",
      "                               | Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1/Relax.1\n",
      "               A_{vt}_{before} : 2.2                                                                 Vertical tail aspect ratio\n",
      "           C_{D_{wm}}_{before} : 0.5                                                                 Windmill drag coefficient\n",
      "       C_{L_{vt,max}}_{before} : 2.6                                                                 Max lift coefficient\n",
      "                  V_1_{before} : 70                                                    [m/s]         Minimum takeoff velocity\n",
      "             V_{land}_{before} : 72                                                    [m/s]         Aircraft Landing Speed\n",
      "         V_{vt_{min}}_{before} : 0.001                                                               Minimum Vertical Tail Volume Coefficient\n",
      "        \\dot{r}_{req}_{before} : 0.1475                                                [1/s²]        Required Yaw Rate at Landing\n",
      "         \\lambda_{vt}_{before} : 0.3                                                                 Vertical tail taper ratio\n",
      "                \\mu_0_{before} : 1.8e-05                                               [N·s/m²]      Dynamic viscosity (SL)\n",
      "            \\rho_{TO}_{before} : 1.225                                                 [kg/m³]       Air density (SL))\n",
      "   \\tan(\\Lambda_{vt})_{before} : 0.4663                                                              Tangent of leading edge sweep\n",
      "        c_{l_{vt,EO}}_{before} : 0.5                                                                 Sectional lift force coefficient (engine out)\n",
      "               e_{vt}_{before} : 0.8                                                                 Span efficiency of vertical tail\n",
      "\n",
      "                               | Mission.1/Aircraft.1/VerticalTail.1/WingBox.4/Relax.1\n",
      "           \\rho_{cap}_{before} : 2700                                                  [kg/m³]       Density of spar cap material\n",
      "           \\rho_{web}_{before} : 2700                                                  [kg/m³]       Density of shear web material\n",
      "   \\sigma_{max,shear}_{before} : 1.67e+08                                              [Pa]          Allowable shear stress\n",
      "         \\sigma_{max}_{before} : 2.5e+08                                               [Pa]          Allowable tensile stress\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                  r_h_{before} : 0.75                                                                Fractional wing thickness at spar web\n",
      "              r_{w/c}_{before} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Wing.1/Relax.1\n",
      "             C_{wing}_{before} : 1                                                                   Wing Weight Margin and Sensitivity Factor\n",
      "            TipReduct_{before} : 1                                                                   Induced Drag Reduction Factor from Wing Tip Devices\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Wing.1/WingBox.3/Relax.1\n",
      "           \\rho_{cap}_{before} : 2700                                                  [kg/m³]       Density of spar cap material\n",
      "           \\rho_{web}_{before} : 2700                                                  [kg/m³]       Density of shear web material\n",
      "   \\sigma_{max,shear}_{before} : 1.67e+08                                              [Pa]          Allowable shear stress\n",
      "         \\sigma_{max}_{before} : 2.5e+08                                               [Pa]          Allowable tensile stress\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                  r_h_{before} : 0.75                                                                Fractional wing thickness at spar web\n",
      "              r_{w/c}_{before} : 0.5                                                                 Wingbox width-to-chord ratio\n",
      "\n",
      "                               | Mission.1/Aircraft.1/Wing.1/WingNoStruct.1/Relax.1\n",
      "        C_{L_{w,max}}_{before} : 2.269                                                               Max lift coefficient, wing\n",
      "             FuelFrac_{before} : 0.9                                                                 Usability Factor of Max Fuel Volume\n",
      "        \\cos(\\Lambda)_{before} : 0.9734                                                              Cosine of quarter-chord sweep angle\n",
      "                 \\eta_{before} : 0.97                                                                Lift efficiency (diff b/w sectional, actual lift)\n",
      "               \\rho_0_{before} : 1.225                                                 [kg/m³]       Air density (0 ft)\n",
      "          \\rho_{fuel}_{before} : 817                                                   [kg/m³]       Density of fuel\n",
      "        \\tan(\\Lambda)_{before} : 0.2352                                                              Tangent of quarter-chord sweep angle\n",
      "         \\tau_{max_w}_{before} : 0.1473                                                              Max allowed wing thickness\n",
      "              b_{max}_{before} : 42.67                                                 [m]           Max Wing Span\n",
      "          f_{aileron}_{before} : 0.04                                                                Aileron Fractional Weight\n",
      "             f_{flap}_{before} : 0.2                                                                 Flap Fractional Weight\n",
      "             f_{lete}_{before} : 0.1                                                                 Lete Fractional Weight\n",
      "             f_{ribs}_{before} : 0.15                                                                Rib Fractional Weight\n",
      "             f_{slat}_{before} : 0.001                                                               Slat Fractional Weight\n",
      "          f_{spoiler}_{before} : 0.02                                                                Spoiler Fractional Weight\n",
      "             f_{watt}_{before} : 0.03                                                                Watt Fractional Weight\n",
      "                    g_{before} : 9.81                                                  [m/s²]        Gravitational acceleration\n",
      "                  wwn_{before} : 0.5                                                                 Wingbox-width-to-chord ratio\n",
      "\n",
      "                               | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/Relax.1\n",
      "            V_{stall}_{before} : [ 120       120       120                             [kt]          Aircraft Stall Speed\n",
      "                                   120       120       120       ]\n",
      "       W_{Load_{max}}_{before} : [ 6.66e+03  6.66e+03  6.66e+03                        [N/m²]        Max Wing Loading\n",
      "                                   6.66e+03  6.66e+03  6.66e+03  ]\n",
      "\n",
      "                               | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/WingPerformance.2/Relax.1\n",
      "            f_{L_{o}}_{before} : [ 0.5       0.5       0.5                                           Center wing lift reduction coefficient\n",
      "                                   0.5       0.5       0.5       ]\n",
      "            f_{L_{t}}_{before} : [ 0.05      0.05      0.05                                          Wing tip lift reduction coefficient\n",
      "                                   0.05      0.05      0.05      ]\n",
      "\n",
      "                               | Mission.1/ClimbSegment.1/FlightState.4/Atmosphere.4/Relax.1\n",
      "                  C_1_{before} : [ 1.46e-06  1.46e-06  1.46e-06                        [kg/K⁰.⁵/m/s] Sutherland coefficient\n",
      "                                   1.46e-06  1.46e-06  1.46e-06  ]\n",
      "              L_{atm}_{before} : [ 0.0065    0.0065    0.0065                          [K/m]         Temperature lapse rate\n",
      "                                   0.0065    0.0065    0.0065    ]\n",
      "              M_{atm}_{before} : [ 0.029     0.029     0.029                           [kg/mol]      Molar mass of dry air\n",
      "                                   0.029     0.029     0.029     ]\n",
      "              R_{atm}_{before} : [ 8.31      8.31      8.31                            [J/K/mol]     air specific heating value\n",
      "                                   8.31      8.31      8.31      ]\n",
      "                  T_s_{before} : [ 110       110       110                             [K]           Sutherland Temperature\n",
      "                                   110       110       110       ]\n",
      "               T_{sl}_{before} : [ 288       288       288                             [K]           Temperature at sea level\n",
      "                                   288       288       288       ]\n",
      "               p_{sl}_{before} : [ 1.01e+05  1.01e+05  1.01e+05                        [Pa]          Pressure at sea level\n",
      "                                   1.01e+05  1.01e+05  1.01e+05  ]\n",
      "\n",
      "                               | Mission.1/ClimbSegment.1/FlightState.4/Relax.1\n",
      "                    R_{before} : [ 287       287       287                             [J/K/kg]      Air Specific Heat\n",
      "                                   287       287       287       ]\n",
      "               \\gamma_{before} : [ 1.4       1.4       1.4                                           Air Specific Heat Ratio\n",
      "                                   1.4       1.4       1.4       ]\n",
      "\n",
      "                               | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/Relax.1\n",
      "            V_{stall}_{before} : [ 120       120                                       [kt]          Aircraft Stall Speed\n",
      "                                   120       120       ]\n",
      "       W_{Load_{max}}_{before} : [ 6.66e+03  6.66e+03                                  [N/m²]        Max Wing Loading\n",
      "                                   6.66e+03  6.66e+03  ]\n",
      "\n",
      "                               | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/WingPerformance.3/Relax.1\n",
      "            f_{L_{o}}_{before} : [ 0.5       0.5                                                     Center wing lift reduction coefficient\n",
      "                                   0.5       0.5       ]\n",
      "            f_{L_{t}}_{before} : [ 0.05      0.05                                                    Wing tip lift reduction coefficient\n",
      "                                   0.05      0.05      ]\n",
      "\n",
      "                               | Mission.1/CruiseSegment.1/FlightState.5/Atmosphere.5/Relax.1\n",
      "                  C_1_{before} : [ 1.46e-06  1.46e-06                                  [kg/K⁰.⁵/m/s] Sutherland coefficient\n",
      "                                   1.46e-06  1.46e-06  ]\n",
      "              L_{atm}_{before} : [ 0.0065    0.0065                                    [K/m]         Temperature lapse rate\n",
      "                                   0.0065    0.0065    ]\n",
      "              M_{atm}_{before} : [ 0.029     0.029                                     [kg/mol]      Molar mass of dry air\n",
      "                                   0.029     0.029     ]\n",
      "              R_{atm}_{before} : [ 8.31      8.31                                      [J/K/mol]     air specific heating value\n",
      "                                   8.31      8.31      ]\n",
      "                  T_s_{before} : [ 110       110                                       [K]           Sutherland Temperature\n",
      "                                   110       110       ]\n",
      "               T_{sl}_{before} : [ 288       288                                       [K]           Temperature at sea level\n",
      "                                   288       288       ]\n",
      "               p_{sl}_{before} : [ 1.01e+05  1.01e+05                                  [Pa]          Pressure at sea level\n",
      "                                   1.01e+05  1.01e+05  ]\n",
      "\n",
      "                               | Mission.1/CruiseSegment.1/FlightState.5/Relax.1\n",
      "                    R_{before} : [ 287       287                                       [J/K/kg]      Air Specific Heat\n",
      "                                   287       287       ]\n",
      "               \\gamma_{before} : [ 1.4       1.4                                                     Air Specific Heat Ratio\n",
      "                                   1.4       1.4       ]\n",
      "\n",
      "                               | Mission.1/FlightState.3/Atmosphere.3/Relax.1\n",
      "                  C_1_{before} : [ 1.46e-06  1.46e-06  1.46e-06  1.46e-06  1.46e-06    [kg/K⁰.⁵/m/s] Sutherland coefficient\n",
      "                                   1.46e-06  1.46e-06  1.46e-06  1.46e-06  1.46e-06  ]\n",
      "              L_{atm}_{before} : [ 0.0065    0.0065    0.0065    0.0065    0.0065      [K/m]         Temperature lapse rate\n",
      "                                   0.0065    0.0065    0.0065    0.0065    0.0065    ]\n",
      "              M_{atm}_{before} : [ 0.029     0.029     0.029     0.029     0.029       [kg/mol]      Molar mass of dry air\n",
      "                                   0.029     0.029     0.029     0.029     0.029     ]\n",
      "              R_{atm}_{before} : [ 8.31      8.31      8.31      8.31      8.31        [J/K/mol]     air specific heating value\n",
      "                                   8.31      8.31      8.31      8.31      8.31      ]\n",
      "                  T_s_{before} : [ 110       110       110       110       110         [K]           Sutherland Temperature\n",
      "                                   110       110       110       110       110       ]\n",
      "               T_{sl}_{before} : [ 288       288       288       288       288         [K]           Temperature at sea level\n",
      "                                   288       288       288       288       288       ]\n",
      "               p_{sl}_{before} : [ 1.01e+05  1.01e+05  1.01e+05  1.01e+05  1.01e+05    [Pa]          Pressure at sea level\n",
      "                                   1.01e+05  1.01e+05  1.01e+05  1.01e+05  1.01e+05  ]\n",
      "\n",
      "                               | Mission.1/FlightState.3/Relax.1\n",
      "                    R_{before} : [ 287       287       287       287       287         [J/K/kg]      Air Specific Heat\n",
      "                                   287       287       287       287       287       ]\n",
      "               \\gamma_{before} : [ 1.4       1.4       1.4       1.4       1.4                       Air Specific Heat Ratio\n",
      "                                   1.4       1.4       1.4       1.4       1.4       ]\n",
      "\n",
      "                               | Mission.1/Relax.1\n",
      "           Fsafetyfac_{before} : 1                                                                   Safety factor on inital climb thrust\n",
      "         MaxClimbTime_{before} : 16                                                    [min]         Total Time in Climb\n",
      "         MinCruiseAlt_{before} : 3.848e+04                                             [ft]          Minimum Cruise Altitude\n",
      "            OPR_{max}_{before} : 35                                                                  Maximum Overall Pressure Ratio\n",
      "              R_{req}_{before} : [ 3e+03     3e+03    ]                                [nmi]         Required Cruise Range\n",
      "\n",
      "Sensitivities\n",
      "-------------\n",
      "                      | Mission.1\n",
      "              R_{req} : [ +0.54     +0.54    ]                               Required Cruise Range\n",
      "         MaxClimbTime : -0.18                                                Total Time in Climb\n",
      "            OPR_{max} : -0.18                                                Maximum Overall Pressure Ratio\n",
      "         MinCruiseAlt : +0.17                                                Minimum Cruise Altitude\n",
      "\n",
      "                      | Mission.1/Aircraft.1\n",
      "   f_{L_{total/wing}} : -1.3                                                 Total lift as a percentage of wing lift\n",
      "           D_{reduct} : +1.2                                                 BLI Drag Reduction Factor\n",
      "              M_{min} : +0.59                                                Minimum Cruise Mach Number\n",
      "      r_{v_{nacelle}} : +0.38                                                Incoming Nacelle Velocity Ratio\n",
      "           C_{engsys} : +0.27                                                Engine System Weight Margin/Sens Factor\n",
      "               V_{ne} : +0.22                                                Never-exceed speed\n",
      "       f_{fuel_{res}} : +0.21                                                Fuel Reserve Fraction\n",
      "            n_{aisle} : +0.14                                                Number of Aisles\n",
      "           \\rho_{T/O} : +0.11                                                Air density at takeoff\n",
      "      r_{S_{nacelle}} : +0.098                                               Nacelle and Pylon Wetted Area\n",
      "        \\Delta x_{CG} : +0.041                                               Max CG Travel Range\n",
      "         f_{wingfuel} : -0.031                                               Fraction of fuel stored in wing tanks\n",
      "             f_{eadd} : +0.021                                               Additional Engine Weight Fraction\n",
      "               n_{vt} : -0.015                                               Number of Vertical Tails\n",
      "           f_{hpesys} : +0.014                                               Power Systems Weight Fraction\n",
      "            f_{pylon} : +0.013                                               Pylong Weight Fraction\n",
      "             SM_{min} : +0.0045                                              Minimum Static Margin\n",
      "              n_{eng} : -0.0044                                              Number of Engines\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1\n",
      "    T_{t_{4.1_{max}}} : -0.22                                                Max turbine inlet temperature\n",
      "        HTR_{f_{SUB}} : -0.12                                                1 - HTRf^2\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1/Combustor.1\n",
      "            C_{p_{c}} : -1.7                                                 Cp Value for Fuel/Air Mix in Combustor\n",
      "            hold_{4a} : -1.5                                                 1+(gamma-1)/2 * M_4a**2\n",
      "             \\eta_{B} : -1.2                                                 Burner Efficiency\n",
      "              \\pi_{b} : -0.36                                                Burner Pressure Ratio\n",
      "          C_{p_{fuel} : +0.063                                               Specific Heat Capacity of Kerosene (~Jet Fuel)\n",
      "              T_{t_f} : -0.024                                               Incoming Fuel Total Temperature\n",
      "             \\alpha_c : +0.0044                                              Total Cooling Flow Bypass Ratio\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1/Compressor.1\n",
      "              \\pi_{d} : -3.3                                                 Diffuser Pressure Ratio\n",
      "             \\pi_{fn} : -2.8                                                 Fan Duct Pressure Loss Ratio\n",
      "           C_{p_{air} : +0.66                                                Cp Value for Air at 250K\n",
      "             C_{p_{2} : +0.63                                                Cp Value for Air at 800K\n",
      "             C_{p_{1} : -0.084                                               Cp Value for Air at 350K\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1/EngineConstants.1\n",
      "          f_{BLI_{P}} : -3.3                                                 BLI Stagnation Pressure Loss Ratio\n",
      "          f_{BLI_{V}} : +2.6                                                 BLI Velocity Loss Ratio\n",
      "          M_{takeoff} : -1.9                                                 1 Minus Percent mass flow loss for de-ice, pressurization, etc.\n",
      "                    g : +1.2                                                 Gravitational Acceleration\n",
      "                    R : +0.06                                                R\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1/EnginePerformance.1/SizingPerformance.1\n",
      "                  dum : [ +0.056    +0.011    +0.015    -0.08     +0.028\n",
      "                          +0.056    +0.011    +0.015    -0.08     +0.028    ]\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1/Thrust.1\n",
      "           C_{p_{fex} : -2                                                   Cp Value for Air at 300K\n",
      "           C_{p_{tex} : -0.14                                                Cp Value for Combustion Products at Core Exhaust\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Engine.1/Turbine.1\n",
      "           C_{p_{t2}} : +1.4                                                 Cp Value for Combustion Products in LP Turbine\n",
      "       \\eta_{LPshaft} : -1.2                                                 Power Transmission Efficiency of Low Pressure Shaft, Smeras in Losses for Electrical Power\n",
      "       \\eta_{HPshaft} : -0.63                                                Power Transmission Efficiency of High Pressure Shaft, Smears in Losses for Electrical Power\n",
      "             \\pi_{tn} : -0.36                                                Turbine Nozzle Pressure Ratio\n",
      "           C_{p_{t1}} : +0.091                                               Cp Value for Combustion Products in HP Turbine\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Fuselage.1\n",
      "W_{avg. pass_{total}} : +0.64                                                Average passenger weight including payload\n",
      "             w_{seat} : +0.56                                                Seat width\n",
      "             n_{pass} : [ +0.47     +0.47    ]                               Number of passengers\n",
      "             C_{fuse} : +0.34                                                Fuselage Weight Margin and Sensitivity\n",
      "                  p_s : +0.3                                                 Seat pitch\n",
      "                  SPR : +0.26                                                Number of seats per row\n",
      "               w_{db} : -0.23                                                DB added half-width\n",
      "             f_{padd} : +0.15                                                Other misc weight as fraction of payload weight\n",
      "            w_{aisle} : +0.14                                                Aisle width\n",
      "             l_{nose} : +0.11                                                Nose length\n",
      "                    g : +0.053                                               Acceleration due to gravity\n",
      "             f_{seat} : +0.043                                               Fractional seat weight\n",
      "          \\rho_{skin} : +0.038                                               Skin density\n",
      "        \\sigma_{skin} : -0.037                                               Max allowable skin stress\n",
      "      \\Delta P_{over} : +0.036                                               Cabin overpressure\n",
      "              W_{fix} : +0.033                                               Fixed weights (pilots, cockpit seats, navcom)\n",
      "              w_{sys} : +0.028                                               Width between cabin and skin for systems\n",
      "          W'_{window} : +0.02                                                Weight/length density of windows\n",
      "          W''_{floor} : +0.017                                               Floor weight/area density\n",
      "              f_{apu} : +0.016                                               APU weight as fraction of payload weight\n",
      "     p_{\\lambda_{vt}} : -0.015                                               1 + 2*Tail taper ratio\n",
      "             N_{land} : +0.014                                               Emergency landing load factor\n",
      "        \\sigma_{bend} : -0.013                                               Bending material stress\n",
      "          W''_{insul} : +0.0091                                              Weight/area density of insulation material\n",
      "          \\rho_{bend} : +0.0077                                              Stringer density\n",
      "       \\lambda_{cone} : -0.0074                                              Tailcone radius taper ratio\n",
      "              r_{w/c} : -0.0066                                              Wingbox width-to-chord ratio\n",
      "           f_{string} : +0.006                                               Fractional stringer weight\n",
      "            f_{frame} : +0.0055                                              Fractional frame weight\n",
      "                  r_E : +0.0049                                              Ratio of stringer/skin moduli\n",
      "             f_{fadd} : +0.004                                               Fractional added weight of local reinforcements\n",
      "         \\rho_{floor} : +0.0036                                              Floor material density\n",
      "          \\rho_{cone} : +0.003                                               Cone material density\n",
      "       \\sigma_{floor} : -0.0027                                              Max allowable floor stress\n",
      "            h_{floor} : -0.0027                                              Floor beam height\n",
      "\n",
      "                      | Mission.1/Aircraft.1/HorizontalTail.1\n",
      "               C_{ht} : +0.0019                                              HT Weight Margin and Sensitivity Factor\n",
      "\n",
      "                      | Mission.1/Aircraft.1/HorizontalTail.1/HorizontalTailNoStruct.1\n",
      "         \\lambda_{ht} : +0.86                                                Horizontal tail taper ratio\n",
      "       C_{L_{ht,max}} : +0.046                                               Max lift coefficient\n",
      "   \\tan(\\Lambda_{ht}) : -0.005                                               tangent of horizontal tail sweep\n",
      "\n",
      "                      | Mission.1/Aircraft.1/HorizontalTail.1/WingBox.5\n",
      "                taper : -0.86                                                Taper ratio\n",
      "         \\sigma_{max} : -0.0025                                              Allowable tensile stress\n",
      "                    g : +0.0019                                              Gravitational acceleration\n",
      "           \\rho_{cap} : +0.0013                                              Density of spar cap material\n",
      "              r_{w/c} : -0.0013                                              Wingbox width-to-chord ratio\n",
      "\n",
      "                      | Mission.1/Aircraft.1/LandingGear.1\n",
      "   \\tan(\\theta_{max}) : +0.047                                               Max rotation angle\n",
      "               C_{lg} : +0.032                                               Landing Gear Weight Margin/Sens Factor\n",
      "     \\tan(\\psi_{max}) : -0.031                                               Upper bound on psi\n",
      "            f_{add,m} : +0.021                                               Proportional added weight, main\n",
      "               z_{CG} : +0.019                                               CG height relative to bottom of fuselage\n",
      "              n_{wps} : +0.0075                                              Number of wheels per strut\n",
      "               n_{mg} : +0.0068                                              Number of main gear struts\n",
      "                  N_s : +0.0022                                              Factor of safety\n",
      "            \\rho_{st} : +0.0022                                              Density of 4340 Steel\n",
      "         \\sigma_{y_c} : -0.0022                                              Compressive yield strength 4340 steel\n",
      "                    g : +0.0022                                              Gravitational acceleration\n",
      "         \\lambda_{LG} : +0.0022                                              Ratio of max to static load\n",
      "            f_{add,n} : +0.0011                                              Proportional added weight, nose\n",
      "\n",
      "                      | Mission.1/Aircraft.1/VerticalTail.1\n",
      "               C_{VT} : +0.0064                                              VT Weight Margin and Sensitivity\n",
      "             N_{spar} : +0.0064                                              Number of Spars in Each VT Carrying Stress in 1 in 20 Case\n",
      "               f_{VT} : +0.0018                                              VT Fractional Weight\n",
      "\n",
      "                      | Mission.1/Aircraft.1/VerticalTail.1/VerticalTailNoStruct.1\n",
      "             V_{land} : -0.18                                                Aircraft Landing Speed\n",
      "            \\rho_{TO} : -0.09                                                Air density (SL))\n",
      "        \\dot{r}_{req} : +0.09                                                Required Yaw Rate at Landing\n",
      "       C_{L_{vt,max}} : -0.081                                               Max lift coefficient\n",
      "   \\tan(\\Lambda_{vt}) : -0.0019                                              Tangent of leading edge sweep\n",
      "\n",
      "                      | Mission.1/Aircraft.1/VerticalTail.1/WingBox.4\n",
      "                    g : +0.0064                                              Gravitational acceleration\n",
      "         \\sigma_{max} : -0.0063                                              Allowable tensile stress\n",
      "           \\rho_{cap} : +0.006                                               Density of spar cap material\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Wing.1\n",
      "            TipReduct : +0.36                                                Induced Drag Reduction Factor from Wing Tip Devices\n",
      "             C_{wing} : +0.15                                                Wing Weight Margin and Sensitivity Factor\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Wing.1/WingBox.3\n",
      "         \\sigma_{max} : -0.23                                                Allowable tensile stress\n",
      "                    g : +0.22                                                Gravitational acceleration\n",
      "           \\rho_{cap} : +0.21                                                Density of spar cap material\n",
      "           \\rho_{web} : +0.0096                                              Density of shear web material\n",
      "                  r_h : +0.0096                                              Fractional wing thickness at spar web\n",
      "   \\sigma_{max,shear} : -0.0096                                              Allowable shear stress\n",
      "              r_{w/c} : -0.0066                                              Wingbox width-to-chord ratio\n",
      "\n",
      "                      | Mission.1/Aircraft.1/Wing.1/WingNoStruct.1\n",
      "        \\cos(\\Lambda) : +0.31                                                Cosine of quarter-chord sweep angle\n",
      "         \\tau_{max_w} : -0.07                                                Max allowed wing thickness\n",
      "             f_{flap} : +0.029                                               Flap Fractional Weight\n",
      "        C_{L_{w,max}} : -0.023                                               Max lift coefficient, wing\n",
      "             f_{ribs} : +0.022                                               Rib Fractional Weight\n",
      "             FuelFrac : -0.015                                               Usability Factor of Max Fuel Volume\n",
      "             f_{lete} : +0.015                                               Lete Fractional Weight\n",
      "          f_{aileron} : +0.0058                                              Aileron Fractional Weight\n",
      "        \\tan(\\Lambda) : -0.0056                                              Tangent of quarter-chord sweep angle\n",
      "             f_{watt} : +0.0044                                              Watt Fractional Weight\n",
      "          f_{spoiler} : +0.0029                                              Spoiler Fractional Weight\n",
      "\n",
      "                      | Mission.1/ClimbSegment.1/ClimbP.1/AircraftP.2/WingPerformance.2\n",
      "            f_{L_{o}} : [ +0.00017  +0.00037  +0.0027                        Center wing lift reduction coefficient\n",
      "                          +0.00017  +0.00037  +0.0027   ]\n",
      "\n",
      "                      | Mission.1/ClimbSegment.1/FlightState.4\n",
      "               \\gamma : [ +0.027    +0.023    +0.046                         Air Specific Heat Ratio\n",
      "                          +0.027    +0.023    +0.046    ]\n",
      "                    R : [ +0.027    +0.023    +0.045                         Air Specific Heat\n",
      "                          +0.027    +0.023    +0.045    ]\n",
      "\n",
      "                      | Mission.1/ClimbSegment.1/FlightState.4/Atmosphere.4\n",
      "              L_{atm} : [ -0.024    +0.012    +0.082                         Temperature lapse rate\n",
      "                          -0.024    +0.012    +0.082    ]\n",
      "               p_{sl} : [ +0.049    -0.011    -0.046                         Pressure at sea level\n",
      "                          +0.049    -0.011    -0.046    ]\n",
      "               T_{sl} : [ +0.011    -0.0077   -0.071                         Temperature at sea level\n",
      "                          +0.011    -0.0077   -0.071    ]\n",
      "              R_{atm} : [ -0.013    -0.011    -0.013                         air specific heating value\n",
      "                          -0.013    -0.011    -0.013    ]\n",
      "              M_{atm} : [ +0.013    +0.011    +0.013                         Molar mass of dry air\n",
      "                          +0.013    +0.011    +0.013    ]\n",
      "                  C_1 : [ -0.00063  -0.00056  +0.0016                        Sutherland coefficient\n",
      "                          -0.00064  -0.00056  +0.0017   ]\n",
      "                  T_s : [ +0.00046  +0.0004   -0.0012                        Sutherland Temperature\n",
      "                          +0.00046  +0.0004   -0.0012   ]\n",
      "\n",
      "                      | Mission.1/CruiseSegment.1/CruiseP.1/AircraftP.3/WingPerformance.3\n",
      "            f_{L_{o}} : [ +0.009    +0.009                                   Center wing lift reduction coefficient\n",
      "                          +0.012    +0.012    ]\n",
      "\n",
      "                      | Mission.1/CruiseSegment.1/FlightState.5\n",
      "               \\gamma : [ +0.068    +0.068                                   Air Specific Heat Ratio\n",
      "                          +0.089    +0.089    ]\n",
      "                    R : [ +0.067    +0.067                                   Air Specific Heat\n",
      "                          +0.088    +0.088    ]\n",
      "\n",
      "                      | Mission.1/CruiseSegment.1/FlightState.5/Atmosphere.5\n",
      "               T_{sl} : [ +0.096    +0.096                                   Temperature at sea level\n",
      "                          +0.035    +0.035    ]\n",
      "              L_{atm} : [ -0.076    -0.076                                   Temperature lapse rate\n",
      "                          -0.018    -0.018    ]\n",
      "               p_{sl} : [ +0.036    +0.036                                   Pressure at sea level\n",
      "                          +0.0054   +0.0054   ]\n",
      "              R_{atm} : [ -0.013    -0.013                                   air specific heating value\n",
      "                          -0.013    -0.013    ]\n",
      "              M_{atm} : [ +0.013    +0.013                                   Molar mass of dry air\n",
      "                          +0.013    +0.013    ]\n",
      "                  C_1 : [ +0.0083   +0.0083                                  Sutherland coefficient\n",
      "                          +0.0071   +0.0072   ]\n",
      "                  T_s : [ -0.006    -0.006                                   Sutherland Temperature\n",
      "                          -0.0052   -0.0052   ]\n",
      "\n",
      "                      | Mission.1/FlightState.3\n",
      "               \\gamma : [ +0.027    +0.023    +0.046    +0.068    +0.089     Air Specific Heat Ratio\n",
      "                          +0.027    +0.023    +0.046    +0.068    +0.089    ]\n",
      "                    R : [ +0.027    +0.023    +0.045    +0.067    +0.088     Air Specific Heat\n",
      "                          +0.027    +0.023    +0.045    +0.067    +0.088    ]\n",
      "\n",
      "                      | Mission.1/FlightState.3/Atmosphere.3\n",
      "               T_{sl} : [ +0.011    -0.0077   -0.071    +0.096    +0.035     Temperature at sea level\n",
      "                          +0.011    -0.0077   -0.071    +0.096    +0.035    ]\n",
      "              L_{atm} : [ -0.024    +0.012    +0.082    -0.076    -0.018     Temperature lapse rate\n",
      "                          -0.024    +0.012    +0.082    -0.076    -0.018    ]\n",
      "               p_{sl} : [ +0.049    -0.011    -0.046    +0.036    +0.0053    Pressure at sea level\n",
      "                          +0.049    -0.011    -0.046    +0.036    +0.0054   ]\n",
      "              M_{atm} : [ +0.013    +0.011    +0.013    +0.013    +0.013     Molar mass of dry air\n",
      "                          +0.013    +0.011    +0.013    +0.013    +0.013    ]\n",
      "              R_{atm} : [ -0.013    -0.011    -0.013    -0.013    -0.013     air specific heating value\n",
      "                          -0.013    -0.011    -0.013    -0.013    -0.013    ]\n",
      "                  C_1 : [ -0.00065  -0.00056  +0.0017   +0.0083   +0.0072    Sutherland coefficient\n",
      "                          -0.00064  -0.00056  +0.0017   +0.0083   +0.0071   ]\n",
      "                  T_s : [ +0.00046  +0.0004   -0.0012   -0.006    -0.0052    Sutherland Temperature\n",
      "                          +0.00046  +0.0004   -0.0012   -0.006    -0.0052   ]\n",
      "\n"
     ]
    }
   ],
   "source": [
    "print sol.table()"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "from gpkit.interactive.sankey import Sankey\n"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {
    "scrolled": false
   },
   "outputs": [],
   "source": [
    "#Sankey(m_relax).diagram(m['W_{f_{total}}'])\n",
    "Sankey(m_relax).sorted_by(\"constraints\", 5)\n",
    "#Sankey(m_relax).diagram(left=60, right=90, width=1050)"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "Sankey(m_relax.program.gps[0]).diagram()"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "Sankey(m_relax.program.gps[1]).diagram()"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "Sankey(m_relax.program.gps[3]).diagram()"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "Sankey(m_relax.program.gps[5]).diagram()"
   ]
  },
  {
   "cell_type": "code",
   "execution_count": null,
   "metadata": {},
   "outputs": [],
   "source": [
    "Sankey(m_relax.program.gps[6]).diagram()"
   ]
  }
 ],
 "metadata": {
  "kernelspec": {
   "display_name": "Python 2",
   "language": "python",
   "name": "python2"
  }
 },
 "nbformat": 4,
 "nbformat_minor": 2
}