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config_template.cfg
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config_template.cfg
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%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% %
% SU2 configuration file %
% Case description: _________________________________________________________ %
% Author: ___________________________________________________________________ %
% Institution: ______________________________________________________________ %
% Date: __________ %
% File Version 5.0.0 "Raven" %
% %
%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%
% ------------- DIRECT, ADJOINT, AND LINEARIZED PROBLEM DEFINITION ------------%
%
% Physical governing equations (EULER, NAVIER_STOKES,
% WAVE_EQUATION, HEAT_EQUATION, FEM_ELASTICITY,
% POISSON_EQUATION)
PHYSICAL_PROBLEM= EULER
%
% Specify turbulence model (NONE, SA, SA_NEG, SST)
KIND_TURB_MODEL= NONE
%
% Mathematical problem (DIRECT, CONTINUOUS_ADJOINT)
MATH_PROBLEM= DIRECT
%
% Restart solution (NO, YES)
RESTART_SOL= NO
%
% Regime type (COMPRESSIBLE, INCOMPRESSIBLE)
REGIME_TYPE= COMPRESSIBLE
%
% System of measurements (SI, US)
% International system of units (SI): ( meters, kilograms, Kelvins,
% Newtons = kg m/s^2, Pascals = N/m^2,
% Density = kg/m^3, Speed = m/s,
% Equiv. Area = m^2 )
% United States customary units (US): ( inches, slug, Rankines, lbf = slug ft/s^2,
% psf = lbf/ft^2, Density = slug/ft^3,
% Speed = ft/s, Equiv. Area = ft^2 )
SYSTEM_MEASUREMENTS= SI
% -------------------- COMPRESSIBLE FREE-STREAM DEFINITION --------------------%
%
% Mach number (non-dimensional, based on the free-stream values)
MACH_NUMBER= 0.8
%
% Angle of attack (degrees, only for compressible flows)
AOA= 1.25
%
% Side-slip angle (degrees, only for compressible flows)
SIDESLIP_ANGLE= 0.0
%
% Discard info in the solution and geometry files
% The AoA in the solution and geometry files is critical for design using
% AoA as a design variable.(NO, YES)
DISCARD_INFILES= NO
%
% Activate fixed lift mode (specify a CL instead of AoA, NO/YES)
FIXED_CL_MODE= NO
%
% Target coefficient of lift for fixed lift mode (0.80 by default)
TARGET_CL= 0.80
%
% Init option to choose between Reynolds (default) or thermodynamics quantities
% for initializing the solution (REYNOLDS, TD_CONDITIONS)
INIT_OPTION= REYNOLDS
%
% Free-stream option to choose between density and temperature (default) for
% initializing the solution (TEMPERATURE_FS, DENSITY_FS)
FREESTREAM_OPTION= TEMPERATURE_FS
%
% Free-stream pressure (101325.0 N/m^2, 2116.216 psf by default)
FREESTREAM_PRESSURE= 101325.0
%
% Free-stream temperature (288.15 K, 518.67 R by default)
FREESTREAM_TEMPERATURE= 288.15
%
% Reynolds number (non-dimensional, based on the free-stream values)
REYNOLDS_NUMBER= 6.5E6
%
% Reynolds length (1 m, 1 inch by default)
REYNOLDS_LENGTH= 1.0
% -------------------------- CL & CM DRIVER DEFINITION ------------------------%
%
% Estimation of dCL/dAlpha (0.2 per degree by default)
DCL_DALPHA= 0.2
%
% Estimation dCD/dCL (0.07 by default)
DCD_DCL_VALUE= 0.07
%
% Number of times Alpha is updated in a fix CL problem (5 by default)
UPDATE_ALPHA= 5
%
% Evaluate DeltaC_D/DeltaC_X during runtime (YES) or use the provided numbers (NO).
EVAL_DCD_DCX= NO
% -------------------- INCOMPRESSIBLE FREE-STREAM DEFINITION ------------------%
%
% Free-stream density (1.2886 Kg/m^3, 0.0025 slug/ft^3 by default)
FREESTREAM_DENSITY= 1.2886
%
% Free-stream velocity (1.0 m/s, 1.0 ft/s by default)
FREESTREAM_VELOCITY= ( 1.0, 0.00, 0.00 )
%
% Free-stream viscosity (1.853E-5 N s/m^2, 3.87E-7 lbf s/ft^2 by default)
FREESTREAM_VISCOSITY= 1.853E-5
% ---------------------- REFERENCE VALUE DEFINITION ---------------------------%
%
% Reference origin for moment computation (m or in)
REF_ORIGIN_MOMENT_X = 0.25
REF_ORIGIN_MOMENT_Y = 0.00
REF_ORIGIN_MOMENT_Z = 0.00
%
% Reference length for pitching, rolling, and yawing non-dimensional
% moment (m or in)
REF_LENGTH_MOMENT= 1.0
%
% Reference area for force coefficients (0 implies automatic
% calculation) (m^2 or in^2)
REF_AREA= 1.0
%
% Flow non-dimensionalization (DIMENSIONAL, FREESTREAM_PRESS_EQ_ONE,
% FREESTREAM_VEL_EQ_MACH, FREESTREAM_VEL_EQ_ONE)
REF_DIMENSIONALIZATION= DIMENSIONAL
% ---- IDEAL GAS, POLYTROPIC, VAN DER WAALS AND PENG ROBINSON CONSTANTS -------%
%
% Different gas model (STANDARD_AIR, IDEAL_GAS, VW_GAS, PR_GAS)
FLUID_MODEL= STANDARD_AIR
%
% Ratio of specific heats (1.4 default and the value is hardcoded
% for the model STANDARD_AIR)
GAMMA_VALUE= 1.4
%
% Specific gas constant (287.058 J/kg*K default and this value is hardcoded
% for the model STANDARD_AIR)
GAS_CONSTANT= 287.058
%
% Critical Temperature (131.00 K by default)
CRITICAL_TEMPERATURE= 131.00
%
% Critical Pressure (3588550.0 N/m^2 by default)
CRITICAL_PRESSURE= 3588550.0
%
% Critical Density (263.0 Kg/m3 by default)
CRITICAL_DENSITY= 263.0
%
% Acentri factor (0.035 (air))
ACENTRIC_FACTOR= 0.035
% --------------------------- VISCOSITY MODEL ---------------------------------%
%
% Viscosity model (SUTHERLAND, CONSTANT_VISCOSITY).
VISCOSITY_MODEL= SUTHERLAND
%
% Molecular Viscosity that would be constant (1.716E-5 by default)
MU_CONSTANT= 1.716E-5
%
% Sutherland Viscosity Ref (1.716E-5 default value for AIR SI)
MU_REF= 1.716E-5
%
% Sutherland Temperature Ref (273.15 K default value for AIR SI)
MU_T_REF= 273.15
%
% Sutherland constant (110.4 default value for AIR SI)
SUTHERLAND_CONSTANT= 110.4
% --------------------------- THERMAL CONDUCTIVITY MODEL ----------------------%
%
% Conductivity model (CONSTANT_CONDUCTIVITY, CONSTANT_PRANDTL).
CONDUCTIVITY_MODEL= CONSTANT_PRANDTL
%
% Molecular Thermal Conductivity that would be constant (0.0257 by default)
KT_CONSTANT= 0.0257
% ------------------------- UNSTEADY SIMULATION -------------------------------%
%
% Unsteady simulation (NO, TIME_STEPPING, DUAL_TIME_STEPPING-1ST_ORDER,
% DUAL_TIME_STEPPING-2ND_ORDER, HARMONIC_BALANCE)
UNSTEADY_SIMULATION= NO
%
% Time Step for dual time stepping simulations (s) -- Only used when UNST_CFL_NUMBER = 0.0
UNST_TIMESTEP= 0.0
%
% Total Physical Time for dual time stepping simulations (s)
UNST_TIME= 50.0
%
% Unsteady Courant-Friedrichs-Lewy number of the finest grid
UNST_CFL_NUMBER= 0.0
%
% Number of internal iterations (dual time method)
UNST_INT_ITER= 200
%
% Iteration number to begin unsteady restarts
UNST_RESTART_ITER= 0
% ----------------------- DYNAMIC MESH DEFINITION -----------------------------%
%
% Dynamic mesh simulation (NO, YES)
GRID_MOVEMENT= NO
%
% Type of dynamic mesh (NONE, RIGID_MOTION, DEFORMING, ROTATING_FRAME,
% MOVING_WALL, STEADY_TRANSLATION, FLUID_STRUCTURE,
% AEROELASTIC, ELASTICITY, EXTERNAL,
% AEROELASTIC_RIGID_MOTION, GUST)
GRID_MOVEMENT_KIND= DEFORMING
%
% Motion mach number (non-dimensional). Used for initializing a viscous flow
% with the Reynolds number and for computing force coeffs. with dynamic meshes.
MACH_MOTION= 0.8
%
% Moving wall boundary marker(s) (NONE = no marker, ignored for RIGID_MOTION)
MARKER_MOVING= ( NONE )
%
% Coordinates of the motion origin
MOTION_ORIGIN_X= 0.25
MOTION_ORIGIN_Y= 0.0
MOTION_ORIGIN_Z= 0.0
%
% Angular velocity vector (rad/s) about the motion origin
ROTATION_RATE_X = 0.0
ROTATION_RATE_Y = 0.0
ROTATION_RATE_Z = 0.0
%
% Pitching angular freq. (rad/s) about the motion origin
PITCHING_OMEGA_X= 0.0
PITCHING_OMEGA_Y= 0.0
PITCHING_OMEGA_Z= 106.69842
%
% Pitching amplitude (degrees) about the motion origin
PITCHING_AMPL_X= 0.0
PITCHING_AMPL_Y= 0.0
PITCHING_AMPL_Z= 1.01
%
% Pitching phase offset (degrees) about the motion origin
PITCHING_PHASE_X= 0.0
PITCHING_PHASE_Y= 0.0
PITCHING_PHASE_Z= 0.0
%
% Translational velocity (m/s) in the x, y, & z directions
TRANSLATION_RATE_X = 0.0
TRANSLATION_RATE_Y = 0.0
TRANSLATION_RATE_Z = 0.0
%
% Plunging angular freq. (rad/s) in x, y, & z directions
PLUNGING_OMEGA_X= 0.0
PLUNGING_OMEGA_Y= 0.0
PLUNGING_OMEGA_Z= 0.0
%
% Plunging amplitude (m) in x, y, & z directions
PLUNGING_AMPL_X= 0.0
PLUNGING_AMPL_Y= 0.0
PLUNGING_AMPL_Z= 0.0
%
% Move Motion Origin for marker moving (1 or 0)
MOVE_MOTION_ORIGIN = 0
% -------------- AEROELASTIC SIMULATION (Typical Section Model) ---------------%
%
% Activated by GRID_MOVEMENT_KIND option
%
% The flutter speed index (modifies the freestream condition in the solver)
FLUTTER_SPEED_INDEX = 0.6
%
% Natural frequency of the spring in the plunging direction (rad/s)
PLUNGE_NATURAL_FREQUENCY = 100
%
% Natural frequency of the spring in the pitching direction (rad/s)
PITCH_NATURAL_FREQUENCY = 100
%
% The airfoil mass ratio
AIRFOIL_MASS_RATIO = 60
%
% Distance in semichords by which the center of gravity lies behind
% the elastic axis
CG_LOCATION = 1.8
%
% The radius of gyration squared (expressed in semichords)
% of the typical section about the elastic axis
RADIUS_GYRATION_SQUARED = 3.48
%
% Solve the aeroelastic equations every given number of internal iterations
AEROELASTIC_ITER = 3
% --------------------------- GUST SIMULATION ---------------------------------%
%
% Apply a wind gust (NO, YES)
WIND_GUST = NO
%
% Type of gust (NONE, TOP_HAT, SINE, ONE_M_COSINE, VORTEX, EOG)
GUST_TYPE = NONE
%
% Direction of the gust (X_DIR or Y_DIR)
GUST_DIR = Y_DIR
%
% Gust wavelenght (meters)
GUST_WAVELENGTH= 10.0
%
% Number of gust periods
GUST_PERIODS= 1.0
%
% Gust amplitude (m/s)
GUST_AMPL= 10.0
%
% Time at which to begin the gust (sec)
GUST_BEGIN_TIME= 0.0
%
% Location at which the gust begins (meters) */
GUST_BEGIN_LOC= 0.0
% ------------------------ SUPERSONIC SIMULATION ------------------------------%
%
% Evaluate equivalent area on the Near-Field (NO, YES)
EQUIV_AREA= NO
%
% Integration limits of the equivalent area ( xmin, xmax, Dist_NearField )
EA_INT_LIMIT= ( 1.6, 2.9, 1.0 )
%
% Equivalent area scale factor ( EA should be ~ force based objective functions )
EA_SCALE_FACTOR= 1.0
%
% Fix an azimuthal line due to misalignments of the near-field
FIX_AZIMUTHAL_LINE= 90.0
%
% Drag weight in sonic boom Objective Function (from 0.0 to 1.0)
DRAG_IN_SONICBOOM= 0.0
% -------------------------- ENGINE SIMULATION --------------------------------%
%
% Highlite area to compute MFR (1 in2 by default)
HIGHLITE_AREA= 1.0
%
% Fan polytropic efficiency (1.0 by default)
FAN_POLY_EFF= 1.0
%
% Only half engine is in the computational grid (NO, YES)
ENGINE_HALF_MODEL= NO
%
% Damping factor for the engine inflow.
DAMP_ENGINE_INFLOW= 0.95
%
% Damping factor for the engine exhaust.
DAMP_ENGINE_EXHAUST= 0.95
%
% Engine nu factor (SA model).
ENGINE_NU_FACTOR= 3.0
%
% Definition of the actuator disk with a double surface (NO, YES)
ACTDISK_DOUBLE_SURFACE= NO
%
% Divide the Actuator Disk surface in SU2_DEF to write a double surface .su2 file (NO, YES)
ACTDISK_SU2_DEF= NO
%
% Mass flow rate of the secondary flow (percentage of the main flow, 0% by default)
ACTDISK_SECONDARY_FLOW= 0
%
% Actuator disk jump definition using ratio or difference (DIFFERENCE, RATIO)
ACTDISK_JUMP= DIFFERENCE
%
% Number of times BC Thrust is updated in a fix Net Thrust problem (5 by default)
UPDATE_BCTHRUST= 10
%
% Initial BC Thrust guess for POWER or D-T driver (4000.0 lbf by default)
INITIAL_BCTHRUST= 4000.0
%
% Distortion rack definition (number of radial probes, degrees)
DISTORTION_RACK= (5, 45)
%
% Initialization with a subsonic flow around the engine.
SUBSONIC_ENGINE= NO
%
% Axis of the cylinder that defines the subsonic region (A_X, A_Y, A_Z, B_X, B_Y, B_Z, Radius)
SUBSONIC_ENGINE_CYL= ( 0.0, 0.0, 0.0, 1.0, 0.0 , 0.0, 1.0 )
%
% Flow variables that define the subsonic region (Mach, Alpha, Beta, Pressure, Temperature)
SUBSONIC_ENGINE_VALUES= ( 0.4, 0.0, 0.0, 2116.216, 518.67 )
% --------------------- INVERSE DESIGN SIMULATION -----------------------------%
%
% Evaluate an inverse design problem using Cp (NO, YES)
INV_DESIGN_CP= NO
%
% Evaluate an inverse design problem using heat flux (NO, YES)
INV_DESIGN_HEATFLUX= NO
% -------------------- BOUNDARY CONDITION DEFINITION --------------------------%
%
% Euler wall boundary marker(s) (NONE = no marker)
MARKER_EULER= ( airfoil )
%
% Navier-Stokes (no-slip), constant heat flux wall marker(s) (NONE = no marker)
% Format: ( marker name, constant heat flux (J/m^2), ... )
MARKER_HEATFLUX= ( NONE )
%
% Navier-Stokes (no-slip), isothermal wall marker(s) (NONE = no marker)
% Format: ( marker name, constant wall temperature (K), ... )
MARKER_ISOTHERMAL= ( NONE )
%
% Far-field boundary marker(s) (NONE = no marker)
MARKER_FAR= ( farfield )
%
% Symmetry boundary marker(s) (NONE = no marker)
MARKER_SYM= ( NONE )
%
% Internal boundary marker(s) e.g. no boundary condition (NONE = no marker)
MARKER_INTERNAL= ( NONE )
%
% Near-Field boundary marker(s) (NONE = no marker)
MARKER_NEARFIELD= ( NONE )
%
% Zone interface boundary marker(s) (NONE = no marker)
MARKER_INTERFACE= ( NONE )
%
% Actuator disk boundary type (VARIABLES_JUMP, NET_THRUST, BC_THRUST,
% DRAG_MINUS_THRUST, MASSFLOW, POWER)
ACTDISK_TYPE= VARIABLES_JUMP
%
% Actuator disk boundary marker(s) with the following formats (NONE = no marker)
% Variables Jump: ( inlet face marker, outlet face marker,
% Takeoff pressure jump (psf), Takeoff temperature jump (R), Takeoff rev/min,
% Cruise pressure jump (psf), Cruise temperature jump (R), Cruise rev/min )
% Net Thrust: ( inlet face marker, outlet face marker,
% Takeoff net thrust (lbs), 0.0, Takeoff rev/min,
% Cruise net thrust (lbs), 0.0, Cruise rev/min )
% BC Thrust: ( inlet face marker, outlet face marker,
% Takeoff BC thrust (lbs), 0.0, Takeoff rev/min,
% Cruise BC thrust (lbs), 0.0, Cruise rev/min )
% Drag-Thrust: ( inlet face marker, outlet face marker,
% Takeoff Drag-Thrust (lbs), 0.0, Takeoff rev/min,
% Cruise Drag-Thrust (lbs), 0.0, Cruise rev/min )
% MasssFlow: ( inlet face marker, outlet face marker,
% Takeoff massflow (lbs/s), 0.0, Takeoff rev/min,
% Cruise massflowt (lbs/s), 0.0, Cruise rev/min )
% Power: ( inlet face marker, outlet face marker,
% Takeoff power (HP), 0.0, Takeoff rev/min
% Cruise power (HP), 0.0, Cruise rev/min )
MARKER_ACTDISK= ( NONE )
%
% Inlet boundary type (TOTAL_CONDITIONS, MASS_FLOW)
INLET_TYPE= TOTAL_CONDITIONS
%
% Inlet boundary marker(s) with the following formats (NONE = no marker)
% Total Conditions: (inlet marker, total temp, total pressure, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
% Mass Flow: (inlet marker, density, velocity magnitude, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
% Incompressible: (inlet marker, NULL, velocity magnitude, flow_direction_x,
% flow_direction_y, flow_direction_z, ... ) where flow_direction is
% a unit vector.
MARKER_INLET= ( NONE )
%
% Supersonic inlet boundary marker(s) (NONE = no marker)
% Format: (inlet marker, temperature, static pressure, velocity_x,
% velocity_y, velocity_z, ... ), i.e. primitive variables specified.
MARKER_SUPERSONIC_INLET= ( NONE )
%
% Outlet boundary marker(s) (NONE = no marker)
% Format: ( outlet marker, back pressure (static), ... )
MARKER_OUTLET= ( NONE )
%
% Supersonic outlet boundary marker(s) (NONE = no marker)
MARKER_SUPERSONIC_OUTLET= ( NONE )
%
% Periodic boundary marker(s) (NONE = no marker)
% Format: ( periodic marker, donor marker, rotation_center_x, rotation_center_y,
% rotation_center_z, rotation_angle_x-axis, rotation_angle_y-axis,
% rotation_angle_z-axis, translation_x, translation_y, translation_z, ... )
MARKER_PERIODIC= ( NONE )
%
% Engine Inflow boundary type (FAN_FACE_MACH, FAN_FACE_PRESSURE, FAN_FACE_MDOT)
ENGINE_INFLOW_TYPE= FAN_FACE_MACH
%
% Engine inflow boundary marker(s) (NONE = no marker)
% Format: (engine inflow marker, fan face Mach, ... )
MARKER_ENGINE_INFLOW= ( NONE )
%
% Engine exhaust boundary marker(s) with the following formats (NONE = no marker)
% Format: (engine exhaust marker, total nozzle temp, total nozzle pressure, ... )
MARKER_ENGINE_EXHAUST= ( NONE )
%
% Displacement boundary marker(s) (NONE = no marker)
% Format: ( displacement marker, displacement value normal to the surface, ... )
MARKER_NORMAL_DISPL= ( NONE )
%
% Load boundary marker(s) (NONE = no marker)
% Format: ( load marker, force value normal to the surface, ... )
MARKER_NORMAL_LOAD= ( NONE )
%
% Pressure boundary marker(s) (NONE = no marker)
% Format: ( pressure marker )
MARKER_PRESSURE= ( NONE )
%
% Neumann bounday marker(s) (NONE = no marker)
MARKER_NEUMANN= ( NONE )
%
% Dirichlet boundary marker(s) (NONE = no marker)
MARKER_DIRICHLET= ( NONE )
%
% Riemann boundary marker(s) (NONE = no marker)
% Format: (marker, data kind flag, list of data)
MARKER_RIEMANN= ( NONE )
%
% Non Reflecting boundary conditions marker(s) (NONE = no marker)
% Format: (marker, data kind flag, list of data)
MARKER_NRBC= ( NONE )
% ------------------------ SURFACES IDENTIFICATION ----------------------------%
%
% Marker(s) of the surface in the surface flow solution file
MARKER_PLOTTING = ( airfoil )
%
% Marker(s) of the surface where the non-dimensional coefficients are evaluated.
MARKER_MONITORING = ( airfoil )
%
% Marker(s) of the surface where obj. func. (design problem) will be evaluated
MARKER_DESIGNING = ( airfoil )
%
% Marker(s) of the surface that is going to be analyzed in detail (massflow, average pressure, distortion, etc)
MARKER_ANALYZE = ( airfoil )
% ------------- COMMON PARAMETERS DEFINING THE NUMERICAL METHOD ---------------%
%
% Numerical method for spatial gradients (GREEN_GAUSS, WEIGHTED_LEAST_SQUARES)
NUM_METHOD_GRAD= GREEN_GAUSS
%
% CFL number (stating value for the adaptive CFL number)
CFL_NUMBER= 10.0
%
% Adaptive CFL number (NO, YES)
CFL_ADAPT= NO
%
% Parameters of the adaptive CFL number (factor down, factor up, CFL min value,
% CFL max value )
CFL_ADAPT_PARAM= ( 1.5, 0.5, 1.25, 50.0 )
%
% Maximum Delta Time in local time stepping simulations
MAX_DELTA_TIME= 1E6
%
% Runge-Kutta alpha coefficients
RK_ALPHA_COEFF= ( 0.66667, 0.66667, 1.000000 )
%
% Objective function in optimization problem (DRAG, LIFT, SIDEFORCE, MOMENT_X,
% MOMENT_Y, MOMENT_Z, EFFICIENCY,
% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
% FORCE_X, FORCE_Y, FORCE_Z, THRUST,
% TORQUE, FREE_SURFACE, TOTAL_HEATFLUX,
% MAXIMUM_HEATFLUX, INVERSE_DESIGN_PRESSURE,
% INVERSE_DESIGN_HEATFLUX, AVG_TOTAL_PRESSURE,
% MASS_FLOW_RATE)
OBJECTIVE_FUNCTION= DRAG
% ----------------------- SLOPE LIMITER DEFINITION ----------------------------%
%
% Reference element length for computing the slope and sharp edges
% limiters (0.1 m, 5.0 in by default)
REF_ELEM_LENGTH= 0.1
%
% Coefficient for the limiter
LIMITER_COEFF= 0.3
%
% Freeze the value of the limiter after a number of iterations
LIMITER_ITER= 999999
%
% Coefficient for the sharp edges limiter
SHARP_EDGES_COEFF= 3.0
%
% Reference coefficient (sensitivity) for detecting sharp edges.
REF_SHARP_EDGES= 3.0
%
% Remove sharp edges from the sensitivity evaluation (NO, YES)
SENS_REMOVE_SHARP= NO
% ------------------------ LINEAR SOLVER DEFINITION ---------------------------%
%
% Linear solver or smoother for implicit formulations (BCGSTAB, FGMRES, SMOOTHER_JACOBI,
% SMOOTHER_ILU0, SMOOTHER_LUSGS,
% SMOOTHER_LINELET)
LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (ILU0, LU_SGS, LINELET, JACOBI)
LINEAR_SOLVER_PREC= LU_SGS
%
% Minimum error of the linear solver for implicit formulations
LINEAR_SOLVER_ERROR= 1E-4
%
% Max number of iterations of the linear solver for the implicit formulation
LINEAR_SOLVER_ITER= 5
% -------------------------- MULTIGRID PARAMETERS -----------------------------%
%
% Multi-grid levels (0 = no multi-grid)
MGLEVEL= 0
%
% Multi-grid cycle (V_CYCLE, W_CYCLE, FULLMG_CYCLE)
MGCYCLE= V_CYCLE
%
% Multi-grid pre-smoothing level
MG_PRE_SMOOTH= ( 1, 2, 3, 3 )
%
% Multi-grid post-smoothing level
MG_POST_SMOOTH= ( 0, 0, 0, 0 )
%
% Jacobi implicit smoothing of the correction
MG_CORRECTION_SMOOTH= ( 0, 0, 0, 0 )
%
% Damping factor for the residual restriction
MG_DAMP_RESTRICTION= 0.75
%
% Damping factor for the correction prolongation
MG_DAMP_PROLONGATION= 0.75
% -------------------- FLOW NUMERICAL METHOD DEFINITION -----------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, CUSP, ROE, AUSM, HLLC,
% TURKEL_PREC, MSW)
CONV_NUM_METHOD_FLOW= ROE
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
SPATIAL_ORDER_FLOW= 2ND_ORDER_LIMITER
%
% Slope limiter (VENKATAKRISHNAN, BARTH_JESPERSEN)
SLOPE_LIMITER_FLOW= VENKATAKRISHNAN
%
% Entropy fix coefficient (0.0 implies no entropy fixing, 1.0 implies scalar
% artificial dissipation)
ENTROPY_FIX_COEFF= 0.001
%
% 1st, 2nd and 4th order artificial dissipation coefficients
AD_COEFF_FLOW= ( 0.15, 0.5, 0.02 )
%
% Viscous limiter (NO, YES)
VISCOUS_LIMITER_FLOW= NO
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT, EULER_EXPLICIT)
TIME_DISCRE_FLOW= EULER_IMPLICIT
%
% Relaxation coefficient
RELAXATION_FACTOR_FLOW= 0.95
% -------------------- TURBULENT NUMERICAL METHOD DEFINITION ------------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_TURB= SCALAR_UPWIND
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
SPATIAL_ORDER_TURB= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_TURB= VENKATAKRISHNAN
%
% Viscous limiter (NO, YES)
VISCOUS_LIMITER_TURB= NO
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_TURB= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the turbulence problem
CFL_REDUCTION_TURB= 1.0
%
% Relaxation coefficient
RELAXATION_FACTOR_TURB= 0.95
% --------------------- HEAT NUMERICAL METHOD DEFINITION ----------------------%
%
% Value of the thermal diffusivity
THERMAL_DIFFUSIVITY= 1.0
% ---------------- ADJOINT-FLOW NUMERICAL METHOD DEFINITION -------------------%
%
% Convective numerical method (JST, LAX-FRIEDRICH, ROE)
CONV_NUM_METHOD_ADJFLOW= JST
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
SPATIAL_ORDER_ADJFLOW= 2ND_ORDER
%
% Slope limiter (VENKATAKRISHNAN, SHARP_EDGES, WALL_DISTANCE)
SLOPE_LIMITER_ADJFLOW= VENKATAKRISHNAN
%
% 1st, 2nd, and 4th order artificial dissipation coefficients
AD_COEFF_ADJFLOW= ( 0.15, 0.5, 0.02 )
%
% Time discretization (RUNGE-KUTTA_EXPLICIT, EULER_IMPLICIT)
TIME_DISCRE_ADJFLOW= EULER_IMPLICIT
%
% Relaxation coefficient
RELAXATION_FACTOR_ADJFLOW= 1.0
%
% Reduction factor of the CFL coefficient in the adjoint problem
CFL_REDUCTION_ADJFLOW= 0.8
%
% Limit value for the adjoint variable
LIMIT_ADJFLOW= 1E6
%
% Multigrid adjoint problem (NO, YES)
MG_ADJFLOW= YES
% ---------------- ADJOINT-TURBULENT NUMERICAL METHOD DEFINITION --------------%
%
% Convective numerical method (SCALAR_UPWIND)
CONV_NUM_METHOD_ADJTURB= SCALAR_UPWIND
%
% Spatial numerical order integration (1ST_ORDER, 2ND_ORDER, 2ND_ORDER_LIMITER)
%
SPATIAL_ORDER_ADJTURB= 1ST_ORDER
%
% Slope limiter (VENKATAKRISHNAN)
SLOPE_LIMITER_ADJTURB= VENKATAKRISHNAN
%
% Time discretization (EULER_IMPLICIT)
TIME_DISCRE_ADJTURB= EULER_IMPLICIT
%
% Reduction factor of the CFL coefficient in the adjoint turbulent problem
CFL_REDUCTION_ADJTURB= 0.01
% ----------------------- GEOMETRY EVALUATION PARAMETERS ----------------------%
%
% Geometrical evaluation mode (FUNCTION, GRADIENT)
GEO_MODE= FUNCTION
%
% Marker(s) of the surface where geometrical based func. will be evaluated
GEO_MARKER= ( airfoil )
%
% Orientation of airfoil sections (X_AXIS, Y_AXIS, Z_AXIS)
GEO_AXIS_STATIONS= Y_AXIS
%
% Coordinate of the sections
GEO_LOCATION_STATIONS= (0.0, 0.5, 1.0)
%
% Plot loads and Cp distributions on each airfoil section
GEO_PLOT_STATIONS= NO
%
% Number of section cuts to make when calculating wing geometry
GEO_WING_STATIONS= 101
%
% Bounds (X coordinate) for the wing geometry computation (MinValue, MaxValue)
GEO_WING_BOUNDS= (1.5, 3.5)
% ------------------------- GRID ADAPTATION STRATEGY --------------------------%
%
% Kind of grid adaptation (NONE, PERIODIC, FULL, FULL_FLOW, GRAD_FLOW,
% FULL_ADJOINT, GRAD_ADJOINT, GRAD_FLOW_ADJ, ROBUST,
% FULL_LINEAR, COMPUTABLE, COMPUTABLE_ROBUST,
% REMAINING, WAKE, SMOOTHING, SUPERSONIC_SHOCK)
KIND_ADAPT= FULL_FLOW
%
% Percentage of new elements (% of the original number of elements)
NEW_ELEMS= 5
%
% Scale factor for the dual volume
DUALVOL_POWER= 0.5
%
% Adapt the boundary elements (NO, YES)
ADAPT_BOUNDARY= YES
% ----------------------- DESIGN VARIABLE PARAMETERS --------------------------%
%
% Kind of deformation (NO_DEFORMATION, TRANSLATION, ROTATION, SCALE,
% FFD_SETTING, FFD_NACELLE
% FFD_CONTROL_POINT, FFD_CAMBER, FFD_THICKNESS, FFD_TWIST
% FFD_CONTROL_POINT_2D, FFD_CAMBER_2D, FFD_THICKNESS_2D, FFD_TWIST_2D,
% HICKS_HENNE, SURFACE_BUMP)
DV_KIND= FFD_SETTING
%
% Marker of the surface in which we are going apply the shape deformation
DV_MARKER= ( airfoil )
%
% Parameters of the shape deformation
% - NO_DEFORMATION ( 1.0 )
% - TRANSLATION ( x_Disp, y_Disp, z_Disp ), as a unit vector
% - ROTATION ( x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - SCALE ( 1.0 )
% - ANGLE_OF_ATTACK ( 1.0 )
% - FFD_SETTING ( 1.0 )
% - FFD_CONTROL_POINT ( FFD_BoxTag, i_Ind, j_Ind, k_Ind, x_Disp, y_Disp, z_Disp )
% - FFD_NACELLE ( FFD_BoxTag, rho_Ind, theta_Ind, phi_Ind, rho_Disp, phi_Disp )
% - FFD_GULL ( FFD_BoxTag, j_Ind )
% - FFD_ANGLE_OF_ATTACK ( FFD_BoxTag, 1.0 )
% - FFD_CAMBER ( FFD_BoxTag, i_Ind, j_Ind )
% - FFD_THICKNESS ( FFD_BoxTag, i_Ind, j_Ind )
% - FFD_TWIST ( FFD_BoxTag, j_Ind, x_Orig, y_Orig, z_Orig, x_End, y_End, z_End )
% - FFD_CONTROL_POINT_2D ( FFD_BoxTag, i_Ind, j_Ind, x_Disp, y_Disp )
% - FFD_CAMBER_2D ( FFD_BoxTag, i_Ind )
% - FFD_THICKNESS_2D ( FFD_BoxTag, i_Ind )
% - FFD_TWIST_2D ( FFD_BoxTag, x_Orig, y_Orig )
% - HICKS_HENNE ( Lower Surface (0)/Upper Surface (1)/Only one Surface (2), x_Loc )
% - SURFACE_BUMP ( x_Start, x_End, x_Loc )
DV_PARAM= ( 1, 0.5 )
%
% Value of the shape deformation
DV_VALUE= 0.01
% ------------------------ GRID DEFORMATION PARAMETERS ------------------------%
%
% Linear solver or smoother for implicit formulations (FGMRES, RESTARTED_FGMRES, BCGSTAB)
DEFORM_LINEAR_SOLVER= FGMRES
%
% Preconditioner of the Krylov linear solver (ILU0, LU_SGS, JACOBI)
DEFORM_LINEAR_SOLVER_PREC= LU_SGS
%
% Number of smoothing iterations for mesh deformation
DEFORM_LINEAR_ITER= 1000
%
% Number of nonlinear deformation iterations (surface deformation increments)
DEFORM_NONLINEAR_ITER= 1
%
% Print the residuals during mesh deformation to the console (YES, NO)
DEFORM_CONSOLE_OUTPUT= YES
%
% Factor to multiply smallest cell volume for deform tolerance (0.001 default)
DEFORM_TOL_FACTOR = 1E-6
%
% Deformation coefficient (in theory from -1.0 to 0.5, a large value is also valid)
DEFORM_COEFF = 1E6
%
% Type of element stiffness imposed for FEA mesh deformation (INVERSE_VOLUME,
% WALL_DISTANCE, CONSTANT_STIFFNESS)
DEFORM_STIFFNESS_TYPE= INVERSE_VOLUME
%
% Visualize the deformation (NO, YES)
VISUALIZE_DEFORMATION= NO
% -------------------- FREE-FORM DEFORMATION PARAMETERS -----------------------%
%
% Tolerance of the Free-Form Deformation point inversion
FFD_TOLERANCE= 1E-10
%
% Maximum number of iterations in the Free-Form Deformation point inversion
FFD_ITERATIONS= 500
%
% FFD box definition: 3D case (FFD_BoxTag, X1, Y1, Z1, X2, Y2, Z2, X3, Y3, Z3, X4, Y4, Z4,
% X5, Y5, Z5, X6, Y6, Z6, X7, Y7, Z7, X8, Y8, Z8)
% 2D case (FFD_BoxTag, X1, Y1, 0.0, X2, Y2, 0.0, X3, Y3, 0.0, X4, Y4, 0.0,
% 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0, 0.0)
FFD_DEFINITION= (MAIN_BOX, 0.5, 0.25, -0.25, 1.5, 0.25, -0.25, 1.5, 0.75, -0.25, 0.5, 0.75, -0.25, 0.5, 0.25, 0.25, 1.5, 0.25, 0.25, 1.5, 0.75, 0.25, 0.5, 0.75, 0.25)
%
% FFD box degree: 3D case (x_degree, y_degree, z_degree)
% 2D case (x_degree, y_degree, 0)
FFD_DEGREE= (10, 10, 1)
%
% Surface grid continuity at the intersection with the faces of the FFD boxes.
% To keep a particular level of surface continuity, SU2 automatically freezes the right
% number of control point planes (NO_DERIVATIVE, 1ST_DERIVATIVE, 2ND_DERIVATIVE, USER_INPUT)
FFD_CONTINUITY= 2ND_DERIVATIVE
%
% Definition of the FFD planes to be frozen in the FFD (x,y,z) or (r,theta,z) or (r, theta, phi).
% Value from 0 FFD degree in that direction. Pick a value larger than degree if you don't want to fix any plane.
FFD_FIX_I= (0,2,3)
FFD_FIX_J= (0,2,3)
FFD_FIX_K= (0,2,3)
%
% There is a symmetry plane (j=0) for all the FFD boxes (YES, NO)
FFD_SYMMETRY_PLANE= NO
%
% FFD coordinate system (CARTESIAN, CYLINDRICAL, SPHERICAL)
FFD_COORD_SYSTEM= CARTESIAN
%
% Vector from the cartesian axis the cylindrical or spherical axis (using cartesian coordinates)
% Note that the location of the axis will affect the wall curvature of the FFD box as well as the
% design variable effect.
FFD_AXIS= (0.0, 0.0, 0.0)
%
% FFD Blending function: Bezier curves with global support (BEZIER), uniform BSplines with local support (BSPLINE_UNIFORM)
FFD_BLENDING= BEZIER
%
% Order of the BSplines
FFD_BSPLINE_ORDER= 2, 2, 2
%
% --------------------------- CONVERGENCE PARAMETERS --------------------------%
%
% Number of total iterations
EXT_ITER= 999999
%
% Convergence criteria (CAUCHY, RESIDUAL)
%
CONV_CRITERIA= RESIDUAL
%
% Residual reduction (order of magnitude with respect to the initial value)
RESIDUAL_REDUCTION= 5
%
% Min value of the residual (log10 of the residual)
RESIDUAL_MINVAL= -8
%
% Start convergence criteria at iteration number
STARTCONV_ITER= 10
%
% Number of elements to apply the criteria
CAUCHY_ELEMS= 100
%
% Epsilon to control the series convergence
CAUCHY_EPS= 1E-10
%
% Direct function to apply the convergence criteria (LIFT, DRAG, NEARFIELD_PRESS)
CAUCHY_FUNC_FLOW= DRAG
%
% Adjoint function to apply the convergence criteria (SENS_GEOMETRY, SENS_MACH)
CAUCHY_FUNC_ADJFLOW= SENS_GEOMETRY
% ------------------------- INPUT/OUTPUT INFORMATION --------------------------%
%
% Mesh input file
MESH_FILENAME= mesh_NACA0012_inv.su2
%
% Mesh input file format (SU2, CGNS)
MESH_FORMAT= SU2
%
% Mesh output file
MESH_OUT_FILENAME= mesh_out.su2
%
% Restart flow input file
SOLUTION_FLOW_FILENAME= solution_flow.dat
%
% Restart adjoint input file
SOLUTION_ADJ_FILENAME= solution_adj.dat
%
% Output file format (TECPLOT, TECPLOT_BINARY, PARAVIEW,
% FIELDVIEW, FIELDVIEW_BINARY)
OUTPUT_FORMAT= TECPLOT
%
% Output file convergence history (w/o extension)
CONV_FILENAME= history
%
% Output file with the forces breakdown
BREAKDOWN_FILENAME= forces_breakdown.dat
%
% Output file restart flow
RESTART_FLOW_FILENAME= restart_flow.dat
%
% Output file restart adjoint
RESTART_ADJ_FILENAME= restart_adj.dat
%
% Output file flow (w/o extension) variables
VOLUME_FLOW_FILENAME= flow
%
% Output file adjoint (w/o extension) variables
VOLUME_ADJ_FILENAME= adjoint
%
% Output Objective function
VALUE_OBJFUNC_FILENAME= of_eval.dat
%
% Output objective function gradient (using continuous adjoint)
GRAD_OBJFUNC_FILENAME= of_grad.dat
%
% Output file surface flow coefficient (w/o extension)
SURFACE_FLOW_FILENAME= surface_flow
%
% Output file surface adjoint coefficient (w/o extension)
SURFACE_ADJ_FILENAME= surface_adjoint
%
% Writing solution file frequency
WRT_SOL_FREQ= 1000
%
% Writing solution file frequency for physical time steps (dual time)
WRT_SOL_FREQ_DUALTIME= 1
%
% Writing convergence history frequency
WRT_CON_FREQ= 1
%
% Writing convergence history frequency (dual time, only written to screen)
WRT_CON_FREQ_DUALTIME= 10
%
% Output residual values in the solution files
WRT_RESIDUALS= NO
%
% Output limiters values in the solution files
WRT_LIMITERS= NO
%
% Output the sharp edges detector
WRT_SHARPEDGES= NO
%
% Minimize the required output memory
LOW_MEMORY_OUTPUT= NO
%
% Verbosity of console output: NONE removes minor MPI overhead (NONE, HIGH)
CONSOLE_OUTPUT_VERBOSITY= HIGH
% --------------------- OPTIMAL SHAPE DESIGN DEFINITION -----------------------%
%
% Available flow based objective functions or constraint functions
% DRAG, LIFT, SIDEFORCE, EFFICIENCY,
% FORCE_X, FORCE_Y, FORCE_Z,
% MOMENT_X, MOMENT_Y, MOMENT_Z,
% THRUST, TORQUE, FIGURE_OF_MERIT,
% EQUIVALENT_AREA, NEARFIELD_PRESSURE,
% TOTAL_HEATFLUX, MAXIMUM_HEATFLUX,
% INVERSE_DESIGN_PRESSURE, INVERSE_DESIGN_HEATFLUX,
% FREE_SURFACE, AVG_TOTAL_PRESSURE, MASS_FLOW_RATE
%
% Available geometrical based objective functions or constraint functions
% WING_VOLUME, WING_MIN_MAXTHICKNESS, WING_MAX_CHORD, WING_MIN_TOC, WING_MAX_TWIST,
% WING_MAX_CURVATURE, WING_MAX_DIHEDRAL
% MAX_THICKNESS, 1/4_THICKNESS, 1/2_THICKNESS, 3/4_THICKNESS, AREA, AOA, CHORD,
% MAX_THICKNESS_SEC1, MAX_THICKNESS_SEC2, MAX_THICKNESS_SEC3, MAX_THICKNESS_SEC4, MAX_THICKNESS_SEC5,
% 1/4_THICKNESS_SEC1, 1/4_THICKNESS_SEC2, 1/4_THICKNESS_SEC3, 1/4_THICKNESS_SEC4, 1/4_THICKNESS_SEC5,
% 1/2_THICKNESS_SEC1, 1/2_THICKNESS_SEC2, 1/2_THICKNESS_SEC3, 1/2_THICKNESS_SEC4, 1/2_THICKNESS_SEC5,
% 3/4_THICKNESS_SEC1, 3/4_THICKNESS_SEC2, 3/4_THICKNESS_SEC3, 3/4_THICKNESS_SEC4, 3/4_THICKNESS_SEC5,
% AREA_SEC1, AREA_SEC2, AREA_SEC3, AREA_SEC4, AREA_SEC5,
% AOA_SEC1, AOA_SEC2, AOA_SEC3, AOA_SEC4, AOA_SEC5,