f16.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="General Dynamics YF-16" version="2.0" release="ALPHA"
 xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
 xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Erik Hofman, Nikolai V. Chr. </author>
  <filecreationdate> 2001-12-28 </filecreationdate>
  <version> $Revision: 1.93 $ </version>
  <license>
   <licenseName>GPL (General Public License)</licenseName>
   <licenseURL>http://www.gnu.org/licenses/gpl.html</licenseURL>
  </license>
  <description> Models an YF-16 </description>
  <note>
   This model was created using data that is, or has been, publically
   available by means of technical reports, textbooks, image graphs or
   published code. This aircraft description file is in no way related 
   to the manufacturer of the real aircraft.
   Neither the name of (any of) the authors nor the names of (any of) the
   manufacturers may be used to endorse or promote products derived from
   this file.
 
   The data is provided ''as is'' and any express or implied
   warranties, including, but not limitted to the implied warranties of
   merchantability and fitness for a particular purpose are disclaimed.
  </note>
  <reference refID="ISBN 0-7232-3458-2" author="William Green" title="General Dynamics F-16 Dash-1" date="1987"/>
  <reference refID="NASA TP-1538" author="Nguyen, L. T.; Ogburn, M. E.; Gilbert, W. P.; Kibler, K. S.; Brown, P. W.; Deal, P. L."
    title="Simulator study of stall/post-stall characteristics of a fighter airplane with relaxed longitudinal static stability." date="12/1979"/>
  <reference refID="AD A 055417" author="Marchand,Michael A" title="Pitch Rate Flight Control for the F-16 Aircraft to Improve Air-To-Air Combat" date="Dec 1977"/>
  <reference refID="AD A 189675" author="Kassan, Mark W" title="F-16 Simulator for Man-in-the-Loop Testing of Aircraft Control Systems (SIMTACS)" date="Dec 1987"/>
  <reference refID="AFD-070827-032" author="Goddard and Lemm" title="Simulation of the F-16 Lantirn Automatic Terrain Avoidance System" date="Aug 1986"/>
  <reference refID="NASA TN-D-8176" author="Gilbert, W. P.; Nguyen, L. T.; Vangunst, R. W."
    title="Simulator study of the effectiveness of an automatic control system designed to improve the high-angle-of-attack characteristics of a fighter airplane" date="1976"/>
  <reference refID="NASA TP-2857" author="Dale A. Mackall" title="Development and flight test experiences with a flight-crucial digital control system" date="1988"/>
  <reference refID="PW-100 Engine" author="Elodie Roux" title="Turbofan and Turbojet Engines: Database Handbook" date="2007"/>
  <reference refID="Manual" author="Lockheed Martin" title="F-16C/D Block 50 Flight Manual" date="2 December 1996"/>
  <reference refID="Youtube video showing speed brake actuation time (2 secs)" author="MultiplyLeadership's channel"
    title="Air-to-air chase video of F-16 AB light off FTT" date="Oct 20, 2010"/>
  <reference refID="None" author="Richard Murray" title="http://www.cds.caltech.edu/~murray/projects/afosr95-vehicles/models/f16/" date="n/a"/>
  <reference refID="H-1999" author="NASA" title="Dynamic ground effects flight test of an F-15 aircraft" date="n/a"/>
  <reference refID="H-2177" author="NASA" title="Dynamic ground effect for a Cranked Arrow Wing Airplane" date="n/a"/>
  <reference refID="None" author="n/a" title="http://www.codeonemagazine.com/archives/1991/articles/jul_91/july2a_91.html" date="n/a"/>
 </fileheader>

 <metrics>
  <wingarea unit="FT2"> 300 </wingarea>
  <wingspan unit="FT"> 30 </wingspan>
  <chord unit="FT"> 11.32 </chord>
  <htailarea unit="FT2"> 63.7 </htailarea>
  <htailarm unit="FT"> 16.46 </htailarm>
  <vtailarea unit="FT2"> 54.75 </vtailarea>
  <vtailarm unit="FT"> 0 </vtailarm>
  <location name="AERORP" unit="IN">
   <x> -198.4336 </x><!-- -198.4336 = static margin of -0.04 -->
   <y> 0 </y>
   <z> 0 </z>
  </location>
  <location name="EYEPOINT" unit="IN">
   <x> -336.2 </x>
   <y> 0 </y>
   <z> 29.5 </z>
  </location>
  <location name="VRP" unit="IN">
   <x> -180 </x>
   <y> 0 </y>
   <z> 0 </z>
  </location>
 </metrics>

 <mass_balance>
  <ixx unit="SLUG*FT2"> 9496 </ixx>
  <iyy unit="SLUG*FT2"> 55814 </iyy>
  <izz unit="SLUG*FT2"> 63100 </izz>
  <ixy unit="SLUG*FT2"> 0 </ixy>
  <ixz unit="SLUG*FT2"> 982 </ixz>
  <iyz unit="SLUG*FT2"> 0 </iyz>
  <emptywt unit="LBS"> 17400 </emptywt>
  <location name="CG" unit="IN">
   <x> -193 </x>
   <y> 0 </y>
   <z> 0 </z>
  </location>
  <pointmass name="Pilot">
   <weight unit="LBS"> 159 </weight>
   <location name="POINTMASS" unit="IN">
    <x> -336.2 </x>
    <y> 0 </y>
    <z> 0 </z>
   </location>
  </pointmass>
 </mass_balance>

 <ground_reactions>
  <contact type="BOGEY" name="NOSE_LG">
   <location unit="IN">
    <x> -299.6 </x>
    <y> 0 </y>
    <z> -72 </z>
   </location>
   <static_friction> 0.8 </static_friction>
   <dynamic_friction> 0.5 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 17250 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 4250 </damping_coeff>
   <max_steer unit="DEG"> 32 </max_steer><!-- as per manual -->
   <brake_group> NOSE </brake_group>
   <retractable>1</retractable>
  </contact>
  <contact type="BOGEY" name="LEFT_MLG">
   <location unit="IN">
    <x> -158.6 </x>
    <y> -48 </y>
    <z> -71.6 </z>
   </location>
   <static_friction> 0.8 </static_friction>
   <dynamic_friction> 0.5 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 37500 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 7500 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> LEFT </brake_group>
   <retractable>1</retractable>
  </contact>
  <contact type="BOGEY" name="RIGHT_MLG">
   <location unit="IN">
    <x> -158.6 </x>
    <y> 48 </y>
    <z> -71.6 </z>
   </location>
   <static_friction> 0.8 </static_friction>
   <dynamic_friction> 0.5 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT"> 37500 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 7500 </damping_coeff>
   <max_steer unit="DEG"> 0.0 </max_steer>
   <brake_group> RIGHT </brake_group>
   <retractable>1</retractable>
  </contact>
  <contact type="STRUCTURE" name="LEFT_WT">
   <location unit="IN">
    <x> -121.3 </x>
    <y> -189 </y>
    <z> 0 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="RIGHT_WT">
   <location unit="IN">
    <x> -121.3 </x>
    <y> 189 </y>
    <z> 0 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="TOP_VS">
   <location unit="IN">
    <x> -27.2 </x>
    <y> 0 </y>
    <z> 123.2 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="LEFT_VFT">
   <location unit="IN">
    <x> -97.6 </x>
    <y> -24.8 </y>
    <z> -52 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="RIGHT_VFT">
   <location unit="IN">
    <x> -97.6 </x>
    <y> 24.8 </y>
    <z> -52 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="INTAKE">
   <location unit="IN">
    <x> -322.4 </x>
    <y> 0 </y>
    <z> -36.6 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="RADOME">
   <location unit="IN">
    <x> -486.6 </x>
    <y> 0 </y>
    <z> -8.7 </z>
   </location>
   <static_friction> 5.0 </static_friction>
   <dynamic_friction> 4.0 </dynamic_friction>
   <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <damping_coeff_rebound unit="LBS/FT/SEC"> 40000 </damping_coeff_rebound>
  </contact>
 </ground_reactions>

 <external_reactions>
   <force name="pushback" frame="BODY">
  <location unit="IN">
    <x>  -2.98081 </x>
    <y> 0.0 </y>
    <z>  -1.9683 </z>
  </location>
  <direction>
    <x>1</x>
    <y>0</y>
    <z>0</z>
  </direction>
   </force>

   <force name="hook" frame="BODY">
  <location unit="IN">
    <x>  100.669 </x>
    <y> 0.0 </y>
    <z>  -28.818 </z>
  </location>
  <direction>
    <x>  -0.9995 </x>
    <y>   0.0 </y>
    <z>   0.01 </z>
  </direction>
   </force>
 </external_reactions>

 <propulsion>
  <engine file="F100-PW-229">
   <location unit="IN">
    <x> 0 </x>
    <y> 0 </y>
    <z> 0 </z>
   </location>
   <orient unit="DEG">
    <roll> 0.0 </roll>
    <pitch> 0 </pitch>
    <yaw> 0 </yaw>
   </orient>
   <feed>0</feed>
   <feed>1</feed>
   <feed>2</feed>
   <feed>3</feed>
   <feed>4</feed>
   <feed>5</feed>
   <feed>6</feed>
   <thruster file="direct">
    <location unit="IN">
     <x> 500 </x>
     <y> 0 </y>
     <z> 0 </z>
    </location>
    <orient unit="DEG">
     <roll> 0.0 </roll>
     <pitch> 0.0 </pitch>
     <yaw> 0.0 </yaw>
    </orient>
   </thruster>
  </engine>
  <!--
          This is a pseudo fuel system.
          As can be read in manual it should have 12 tanks,
          including possibility for 3 droptanks.
          And engine only draws fuel from 2 of them.

          Total internal JP-4 should be: 6625
          Total external JP-4 should be: 9300 (the big tanks, there is 2 sizes)
  -->
  <tank type="FUEL"> <!-- FWD Tank -->
   <location unit="IN">
    <x> -225 </x>
   <y> 0 </y>
   <z> 0 </z>
   </location>
   <capacity unit="LBS"> 2812.5 </capacity>
   <contents unit="LBS"> 2812.5 </contents>
   <type>JP-4</type>
   <priority> 3 </priority>
  </tank>
  <tank type="FUEL"> <!-- AFT Tank -->
   <location unit="IN">
    <x> -153 </x>
   <y> 0 </y>
   <z> 0 </z>
   </location>
   <capacity unit="LBS"> 2812.5 </capacity>
   <contents unit="LBS"> 2812.5 </contents>
   <type>JP-4</type>
   <priority> 3 </priority>
  </tank>
  <tank type="FUEL"> <!-- Right External Tank -->
   <location unit="IN">
    <x> -213 </x>
   <y> 80 </y>
   <z> -40 </z>
   </location>
   <capacity unit="LBS"> 2991 </capacity>
   <contents unit="LBS"> 0 </contents>
   <type>JP-4</type>
   <priority> 1 </priority>
  </tank>
  <tank type="FUEL"> <!-- Left External Tank -->
   <location unit="IN">
    <x> -213 </x>
   <y> -80 </y>
   <z> -40 </z>
   </location>
   <capacity unit="LBS"> 2991 </capacity>
   <contents unit="LBS"> 0 </contents>
   <type>JP-4</type>
   <priority> 1 </priority>
  </tank>
  <tank type="FUEL"> <!-- Center External Tank -->
   <location unit="IN">
    <x> -213 </x>
   <y>   0 </y>
   <z> -50 </z>
   </location>
   <capacity unit="LBS"> 2425 </capacity>
   <contents unit="LBS"> 0 </contents>
   <type>JP-4</type>
   <priority> 1 </priority>
  </tank>
  <tank type="FUEL"> <!-- Right wing tank -->
   <location unit="IN">
    <x> -193 </x>
   <y>  80 </y>
   <z>   0 </z>
   </location>
   <capacity unit="LBS"> 500 </capacity>
   <contents unit="LBS"> 500 </contents>
   <type>JP-4</type>
   <priority> 2 </priority>
  </tank>
  <tank type="FUEL"> <!-- Left wing tank -->
   <location unit="IN">
    <x> -193 </x>
   <y> -80 </y>
   <z>   0 </z>
   </location>
   <capacity unit="LBS"> 500 </capacity>
   <contents unit="LBS"> 500 </contents>
   <type>JP-4</type>
   <priority> 2 </priority>
  </tank>
 </propulsion>

 <system file="pushback">
   <property>/sim/model/pushback/kp</property>
   <property>/sim/model/pushback/ki</property>
   <property>/sim/model/pushback/kd</property>
 </system>
 <system file="hook"/>
 <flight_control file="Systems/jsb-controls"/>






<aerodynamics>

<!-- begin: aerodynamics by Nikolai V. Chr.

 Note:
======
In all aero tables that do not have author listed, the numbers was typed in by Nikolai V. Chr.
Where nothing else is mentioned the aerodynamics come from TP 1538


 Todo:
======
Make all coefficients functions (like Cy and Cz is)
Put in engine gyroscopic effect (160 slugs-ft2/sec)


 Missing wind-tunnel data:
==========================
+Gear dynamics
 Ground effect
+Wave drag
+Trailing edge flaps dynamics
 Stores dynamics
 Canopy dynamics
 Dynamics of high speed

-->

    <!--<aero_ref_pt_shift_x>
        <function name="metrics/aero-rp-shift-mac">
            <description>
                Mach-tuck: Transonic Shift of Aerodynamic Center

                An estimate by Nikolai V. Chr.

                Default static margin =-0.04c (5.4336 inch)
                Default CoG           = 0.35c
                Chord                 = 11.32 ft

                0.19 makes the AeroRP move to 0.5c at 1.1 mach.

            </description>
            <table name="table/ACshift">
                <independentVar>velocities/mach</independentVar>
                <tableData>
                  0.6 0
                  0.8 0.05
                  1.1 0.19
                </tableData>
            </table>
        </function>
    </aero_ref_pt_shift_x>-->

    <hysteresis_limits unit="DEG">
        <description>Stall regime</description>
        <min> 31 </min>
        <max> 36 </max>
    </hysteresis_limits>

    <function name="aero/CG-pos-c">
        <description>
            CG position
        </description>
        <sum>
            <v>0.35</v><!-- X_CG-ref -->
            <quotient>
                <product>
                    <difference>
                        <p>inertia/cg-x-in</p>
                        <v>-193</v><!-- X_CG-ref (inches) -->
                    </difference>
                    <v>0.083333</v><!-- in to ft -->
                </product>
                <property>metrics/cbarw-ft</property>
            </quotient>
        </sum>
    </function>

    <function name="aero/static-margin-c">
        <description>
            Static margin in fraction of chord
        </description>
        <quotient>
            <product>
                <difference>
                    <p>metrics/aero-rp-x-in</p>
                    <p>inertia/cg-x-in</p>
                </difference>
                <v>0.083333</v><!-- in to ft -->
            </product>
            <property>metrics/cbarw-ft</property>
        </quotient>
    </function>

    <function name="aero/coefficient/CDwave">
        <product>
              <table name="table/CDwave">
                  <independentVar>velocities/mach</independentVar>
                  <tableData>
                      0.000  0.000
                      0.810  0.000
                      1.100  0.028
                      1.800  0.020
                  </tableData>
              </table>
              <table name="table/CDwave_sb">
                  <independentVar>fcs/speedbrake-pos-norm</independentVar>
                  <tableData>
                      0  1.0
                      1  1.5
                  </tableData>
              </table>              
        </product>
    </function>

    <function name="aero/coefficient/CDtef">
        <product>
            <abs>
                <!-- is absolute so -2 degs up don't give negative drag -->
                <property>fcs/fly-by-wire/tef/tef-pos-norm</property>
            </abs>
            <value>0.020</value>
        </product>
    </function>

    <function name="aero/coefficient/CDgear">
        <product>
            <property>gear/gear-pos-norm</property>
            <value>0.025</value>
        </product>
    </function>

    <function name="aero/coefficient/CLtef">
        <product>
            <property>fcs/fly-by-wire/tef/tef-pos-norm</property>
            <value>0.1221731</value>
        </product>
    </function>    

    <function name="aero/coefficient/CL_g">
       <description>Change in lift due to ground effect</description>
       <product>
          <table>
              <independentVar>aero/h_b-mac-ft</independentVar>
              <tableData>
             0.0000  0.2290
             0.2000  0.1240
             0.3000  0.1160
             0.4000  0.1240
             0.6000  0.1050
             0.8000  0.0410
             1.0000  0.0340
             1.2000  0.0190
             1.4000  0.0080
             1.6000  0.0030
             1.8000  0.0010
             2.0000  0.0000
             2.2000  0.0000
              </tableData>
          </table>
          <cos>
              <!-- Less lift due to ground effect when flying inverted-->
              <product>
                  <p>/orientation/roll-deg</p>
                  <v>0.017453</v>
              </product>
          </cos>
       </product>
      </function>

    <function name="aero/coefficient/Cx_g">
        <sum>
            <v>1</v>
            <product>
                <property>aero/coefficient/CL_g</property>
                <sin>
                    <property>aero/alpha-rad</property>
                </sin>
            </product>
        </sum>
    </function>

    <function name="aero/coefficient/Cz_g">
        <sum>
            <v>1</v>
            <product>
                <property>aero/coefficient/CL_g</property>
                <v>-1</v>
                <cos>
                    <property>aero/alpha-rad</property>
                </cos>
            </product>
        </sum>
    </function>

    <axis name="X">

        <function name="aero/coefficient/CDx">
            <description>Drag</description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>              
                <sum>
                    <property>aero/coefficient/CDgear</property>
                    <property>aero/coefficient/CDtef</property>
                    <property>aero/coefficient/CDwave</property>
                </sum>
                <cos>
                  <property>aero/alpha-rad</property>
                </cos>
                <v>-1</v>
            </product>
        </function>        

        <function name="aero/coefficient/CLx">
            <description>Lift</description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>              
                <sum>
                    <property>aero/coefficient/CLtef</property>
                </sum>
                <sin>
                  <property>aero/alpha-rad</property>
                </sin>
            </product>
        </function>

        <function name="aero/coefficient/Cx">
            <description>
               Cx coefficient in body coordinate system.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <p>aero/coefficient/Cx_g</p>
                <table name="table/Cx">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">aero/beta-deg</independentVar>
                    <independentVar lookup="table">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                    <tableData breakPoint="-25.0">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.2028 -0.2176 -0.2098 -0.2100 -0.2165 -0.2133 -0.2096 -0.2085 -0.2092 -0.2102 -0.2135 -0.2138 -0.2135 -0.2128 -0.2106 -0.2040 -0.2038 -0.1992 -0.1969
-15 -0.1891 -0.1948 -0.1984 -0.2034 -0.2029 -0.2051 -0.2075 -0.2075 -0.2103 -0.2099 -0.2129 -0.2101 -0.2092 -0.2066 -0.2058 -0.2064 -0.2013 -0.1977 -0.1920
-10 -0.1701 -0.1809 -0.1889 -0.1921 -0.1895 -0.1891 -0.1907 -0.1939 -0.1983 -0.1988 -0.1979 -0.1932 -0.1911 -0.1908 -0.1897 -0.1923 -0.1891 -0.1810 -0.1702
 -5 -0.1302 -0.1391 -0.1436 -0.1481 -0.1556 -0.1580 -0.1583 -0.1587 -0.1601 -0.1594 -0.1587 -0.1586 -0.1575 -0.1563 -0.1539 -0.1464 -0.1419 -0.1374 -0.1286
  0 -0.1045 -0.1136 -0.1203 -0.1262 -0.1288 -0.1279 -0.1285 -0.1286 -0.1291 -0.1293 -0.1291 -0.1280 -0.1271 -0.1265 -0.1257 -0.1232 -0.1172 -0.1105 -0.1014
  5 -0.0640 -0.0709 -0.0756 -0.0801 -0.0807 -0.0816 -0.0823 -0.0830 -0.0845 -0.0850 -0.0840 -0.0835 -0.0818 -0.0804 -0.0805 -0.0792 -0.0747 -0.0698 -0.0626
 10 -0.0189 -0.0258 -0.0238 -0.0249 -0.0218 -0.0215 -0.0222 -0.0240 -0.0269 -0.0273 -0.0276 -0.0258 -0.0237 -0.0230 -0.0226 -0.0256 -0.0246 -0.0247 -0.0196
 15  0.0248  0.0236  0.0252  0.0258  0.0339  0.0366  0.0402  0.0422  0.0403  0.0403  0.0397  0.0402  0.0393  0.0373  0.0349  0.0268  0.0262  0.0246  0.0258
 20  0.0629  0.0636  0.0628  0.0629  0.0762  0.0783  0.0827  0.0849  0.0864  0.0868  0.0896  0.0849  0.0815  0.0766  0.0715  0.0582  0.0581  0.0589  0.0583
 25  0.1048  0.1063  0.1038  0.0997  0.1037  0.1057  0.1063  0.1075  0.1073  0.1064  0.1075  0.1072  0.1083  0.1060  0.1011  0.0971  0.1012  0.1037  0.1022
 30  0.0909  0.0976  0.0923  0.1018  0.1139  0.1290  0.1364  0.1391  0.1417  0.1410  0.1408  0.1377  0.1347  0.1324  0.1284  0.1164  0.1069  0.1122  0.1054
 35  0.1128  0.1180  0.1220  0.1300  0.1419  0.1434  0.1465  0.1563  0.1626  0.1678  0.1683  0.1677  0.1648  0.1560  0.1454  0.1335  0.1255  0.1215  0.1162
 40  0.1360  0.1505  0.1408  0.1499  0.1630  0.1637  0.1632  0.1724  0.1770  0.1786  0.1748  0.1743  0.1703  0.1650  0.1606  0.1475  0.1384  0.1481  0.1336
 45  0.1611  0.1705  0.1699  0.1697  0.1717  0.1758  0.1753  0.1716  0.1748  0.1728  0.1718  0.1722  0.1696  0.1651  0.1646  0.1627  0.1629  0.1634  0.1541
 50  0.1555  0.1684  0.1762  0.1796  0.1829  0.1820  0.1775  0.1741  0.1756  0.1796  0.1828  0.1853  0.1881  0.1860  0.1868  0.1644  0.1541  0.1513  0.1435
 55  0.1658  0.1720  0.1674  0.1786  0.1920  0.1909  0.1904  0.1888  0.1907  0.1955  0.1883  0.1794  0.1806  0.1867  0.1918  0.1881  0.1416  0.1530  0.1537
 60  0.1617  0.1726  0.1785  0.1644  0.1803  0.1797  0.1947  0.1842  0.1856  0.1861  0.1875  0.1881  0.1885  0.1869  0.1833  0.1577  0.1554  0.1585  0.1566
 70  0.1662  0.1706  0.1747  0.1576  0.1754  0.1764  0.1948  0.1872  0.1900  0.1863  0.1882  0.1888  0.1910  0.1902  0.1870  0.1618  0.1719  0.1707  0.1692
 80  0.1896  0.1817  0.1752  0.1706  0.1704  0.1703  0.1718  0.1770  0.1756  0.1792  0.1766  0.1754  0.1776  0.1748  0.1788  0.1574  0.1571  0.1638  0.1718
 90  0.1928  0.1861  0.1811  0.1854  0.1884  0.1864  0.1894  0.1874  0.1872  0.1859  0.1876  0.1871  0.1876  0.1925  0.1892  0.1715  0.1674  0.1740  0.1825
                    </tableData>
                    <tableData breakPoint="-10.0">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.1435 -0.1424 -0.1492 -0.1459 -0.1447 -0.1403 -0.1341 -0.1322 -0.1295 -0.1296 -0.1319 -0.1320 -0.1325 -0.1330 -0.1355 -0.1367 -0.1400 -0.1332 -0.1343
-15 -0.1269 -0.1298 -0.1288 -0.1261 -0.1229 -0.1229 -0.1223 -0.1230 -0.1237 -0.1241 -0.1238 -0.1240 -0.1235 -0.1231 -0.1237 -0.1269 -0.1296 -0.1306 -0.1277
-10 -0.1059 -0.1107 -0.1109 -0.1112 -0.1102 -0.1109 -0.1113 -0.1124 -0.1135 -0.1188 -0.1136 -0.1125 -0.1118 -0.1104 -0.1110 -0.1120 -0.1117 -0.1115 -0.1067
 -5 -0.0682 -0.0733 -0.0773 -0.0798 -0.0863 -0.0891 -0.0903 -0.0914 -0.0916 -0.0920 -0.0912 -0.0902 -0.0886 -0.0869 -0.0839 -0.0774 -0.0749 -0.0709 -0.0658
  0 -0.0515 -0.0541 -0.0564 -0.0576 -0.0610 -0.0621 -0.0629 -0.0638 -0.0645 -0.0649 -0.0643 -0.0635 -0.0627 -0.0609 -0.0593 -0.0559 -0.0547 -0.0524 -0.0498
  5 -0.0145 -0.0133 -0.0123 -0.0129 -0.0169 -0.0175 -0.0182 -0.0188 -0.0204 -0.0199 -0.0205 -0.0194 -0.0183 -0.0168 -0.0160 -0.0120 -0.0114 -0.0133 -0.0154
 10  0.0245  0.0287  0.0344  0.0376  0.0389  0.0394  0.0385  0.0389  0.0383  0.0376  0.0376  0.0386  0.0392  0.0391  0.0389  0.0376  0.0344  0.0305  0.0245
 15  0.0724  0.0789  0.0876  0.0923  0.0972  0.0995  0.1013  0.1023  0.1022  0.1016  0.1020  0.1016  0.1007  0.0997  0.0972  0.0923  0.0876  0.0789  0.0724
 20  0.1232  0.1285  0.1268  0.1259  0.1336  0.1357  0.1360  0.1359  0.1335  0.1332  0.1342  0.1348  0.1353  0.1320  0.1308  0.1231  0.1240  0.1257  0.1204
 25  0.1401  0.1501  0.1493  0.1481  0.1492  0.1512  0.1512  0.1480  0.1456  0.1434  0.1445  0.1470  0.1484  0.1469  0.1466  0.1455  0.1467  0.1475  0.1375
 30  0.1085  0.1290  0.1326  0.1466  0.1529  0.1648  0.1684  0.1689  0.1692  0.1680  0.1669  0.1672  0.1653  0.1644  0.1622  0.1559  0.1419  0.1383  0.1178
 35  0.1123  0.1202  0.1347  0.1424  0.1571  0.1641  0.1770  0.1837  0.1849  0.1843  0.1841  0.1852  0.1830  0.1797  0.1723  0.1577  0.1499  0.1354  0.1275
 40  0.1397  0.1474  0.1427  0.1518  0.1659  0.1684  0.1787  0.1824  0.1860  0.1860  0.1872  0.1833  0.1772  0.1764  0.1721  0.1580  0.1489  0.1536  0.1459
 45  0.1593  0.1558  0.1589  0.1592  0.1680  0.1685  0.1669  0.1756  0.1739  0.1743  0.1736  0.1725  0.1701  0.1651  0.1641  0.1553  0.1550  0.1519  0.1554
 50  0.1399  0.1466  0.1482  0.1565  0.1641  0.1643  0.1603  0.1574  0.1580  0.1610  0.1622  0.1627  0.1645  0.1626  0.1635  0.1559  0.1476  0.1461  0.1393
 55  0.1435  0.1410  0.1277  0.1380  0.1532  0.1537  0.1541  0.1533  0.1532  0.1560  0.1495  0.1413  0.1423  0.1468  0.1505  0.1353  0.1251  0.1384  0.1408
 60  0.1386  0.1428  0.1420  0.1180  0.1329  0.1331  0.1375  0.1393  0.1423  0.1442  0.1410  0.1369  0.1452  0.1372  0.1360  0.1212  0.1452  0.1459  0.1417
 70  0.1250  0.1253  0.1267  0.1186  0.1239  0.1254  0.1433  0.1368  0.1419  0.1404  0.1371  0.1327  0.1335  0.1353  0.1347  0.1295  0.1376  0.1362  0.1358
 80  0.1291  0.1250  0.1223  0.1211  0.1250  0.1237  0.1235  0.1281  0.1269  0.1309  0.1293  0.1294  0.1325  0.1305  0.1294  0.1240  0.1253  0.1279  0.1320
 90  0.1397  0.1348  0.1318  0.1320  0.1371  0.1359  0.1358  0.1335  0.1346  0.1343  0.1363  0.1363  0.1366  0.1407  0.1367  0.1317  0.1315  0.1345  0.1394
                     </tableData>
                    <tableData breakPoint="0.0">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0       2      4      6      8      10     15     20     25     30
-20 -.1072 -.1061 -.1129 -.1096 -.1084 -.1040 -.0978 -.0959 -.0932 -.0933 -.0956 -.0957 -.0962 -.0967 -.0992 -.1004 -.1037 -.0969 -.0980
-15 -.1006 -.1035 -.1025 -.0998 -.0966 -.0966 -.0960 -.0967 -.0974 -.0978 -.0975 -.0977 -.0972 -.0968 -.0974 -.1006 -.1033 -.1043 -.1014
-10 -.0853 -.0901 -.0903 -.0906 -.0896 -.0903 -.0907 -.0918 -.0929 -.0982 -.0930 -.0919 -.0912 -.0898 -.0904 -.0914 -.0911 -.0909 -.0861
-05 -.0546 -.0597 -.0637 -.0662 -.0727 -.0755 -.0767 -.0778 -.0780 -.0784 -.0776 -.0766 -.0750 -.0733 -.0703 -.0638 -.0613 -.0573 -.0522
 00 -.0355 -.0381 -.0404 -.0416 -.0450 -.0461 -.0469 -.0478 -.0485 -.0489 -.0483 -.0475 -.0467 -.0449 -.0433 -.0399 -.0387 -.0364 -.0338
 05 -.0012 0.0000 0.0010 0.0004 -.0036 -.0042 -.0049 -.0055 -.0071 -.0066 -.0072 -.0061 -.0050 -.0035 -.0027 0.0013 0.0019 0.0000 -.0021
 10 0.0359 0.0491 0.0458 0.0490 0.0503 0.0508 0.0499 0.0509 0.0497 0.0490 0.0490 0.0500 0.0506 0.0505 0.0503 0.0490 0.0458 0.0419 0.0359
 15 0.0780 0.0845 0.0932 0.0979 0.1028 0.1051 0.1069 0.1079 0.1078 0.1072 0.1076 0.1072 0.1063 0.1053 0.1028 0.0979 0.0932 0.0845 0.0780
 20 0.1183 0.1236 0.1219 0.1210 0.1287 0.1308 0.1311 0.1310 0.1286 0.1283 0.1293 0.1299 0.1304 0.1271 0.1259 0.1182 0.1191 0.1208 0.1155
 25 0.1267 0.1367 0.1359 0.1347 0.1358 0.1378 0.1378 0.1346 0.1322 0.1300 0.1311 0.1336 0.1350 0.1335 0.1332 0.1321 0.1333 0.1341 0.1241
 30 0.0941 0.1146 0.1182 0.1322 0.1385 0.1504 0.1540 0.1545 0.1548 0.1536 0.1525 0.1528 0.1509 0.1500 0.1478 0.1415 0.1275 0.1239 0.1034
 35 0.0885 0.0964 0.1109 0.1189 0.1333 0.1391 0.1532 0.1599 0.1611 0.1605 0.1603 0.1614 0.1592 0.1559 0.1485 0.1339 0.1261 0.1116 0.1037
 40 0.1089 0.1166 0.1119 0.1210 0.1351 0.1376 0.1479 0.1516 0.1552 0.1552 0.1564 0.1525 0.1464 0.1456 0.1413 0.1272 0.1181 0.1228 0.1151
 45 0.1232 0.1197 0.1228 0.1231 0.1319 0.1324 0.1308 0.1332 0.1378 0.1382 0.1375 0.1364 0.1340 0.1380 0.1280 0.1192 0.1189 0.1158 0.1193
 50 0.1135 0.1185 0.1184 0.1171 0.1243 0.1279 0.1279 0.1258 0.1257 0.1281 0.1258 0.1228 0.1221 0.1186 0.1180 0.1108 0.1121 0.1122 0.1072
 55 0.1137 0.1195 0.1146 0.1161 0.1209 0.1211 0.1211 0.1195 0.1183 0.1200 0.1185 0.1153 0.1160 0.1152 0.1135 0.1087 0.1072 0.1121 0.1063
 60 0.1037 0.1090 0.1094 0.1049 0.1109 0.1123 0.1181 0.1184 0.1170 0.1147 0.1141 0.1126 0.1129 0.1129 0.1109 0.1049 0.1094 0.1090 0.1037
 70 0.0857 0.0858 0.0857 0.0796 0.0851 0.0919 0.1150 0.1087 0.1089 0.1025 0.1022 0.1007 0.1012 0.0994 0.0952 0.0897 0.0958 0.0959 0.0958
 80 0.0842 0.0807 0.0787 0.0778 0.0791 0.0793 0.0805 0.0846 0.0808 0.0821 0.0802 0.0799 0.0826 0.0800 0.0709 0.0756 0.0765 0.0785 0.0820
 90 0.0847 0.0813 0.0798 0.0824 0.0843 0.0843 0.0853 0.0841 0.0858 0.0864 0.0857 0.0828 0.0817 0.0857 0.0816 0.0797 0.0771 0.0786 0.0820
                    </tableData>
                    <tableData breakPoint="10.0">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.1011 -0.1000 -0.1068 -0.1035 -0.1023 -0.0979 -0.0917 -0.0898 -0.0872 -0.0872 -0.0895 -0.0896 -0.0901 -0.0906 -0.0931 -0.0943 -0.0976 -0.0908 -0.0919
-15 -0.1046 -0.1075 -0.1065 -0.1038 -0.1006 -0.0994 -0.1000 -0.1007 -0.1014 -0.1018 -0.1015 -0.1017 -0.1012 -0.1008 -0.1014 -0.1046 -0.1073 -0.1083 -0.1054
-10 -0.0991 -0.1039 -0.1041 -0.1044 -0.1034 -0.1041 -0.1045 -0.1056 -0.1067 -0.1120 -0.1068 -0.1057 -0.1050 -0.1036 -0.1042 -0.1052 -0.1049 -0.1047 -0.0999
 -5 -0.0694 -0.0745 -0.0785 -0.0810 -0.0875 -0.0903 -0.0915 -0.0926 -0.0928 -0.0932 -0.0924 -0.0914 -0.0898 -0.0881 -0.0851 -0.0786 -0.0761 -0.0721 -0.0670
  0 -0.0501 -0.0527 -0.0550 -0.0562 -0.0596 -0.0607 -0.0615 -0.0624 -0.0631 -0.0635 -0.0629 -0.0621 -0.0613 -0.0595 -0.0579 -0.0545 -0.0533 -0.0510 -0.0484
  5 -0.0180 -0.0168 -0.0158 -0.0164 -0.0204 -0.0210 -0.0217 -0.0223 -0.0239 -0.0234 -0.0240 -0.0229 -0.0218 -0.0203 -0.0195 -0.0155 -0.0149 -0.0168 -0.0189
 10  0.0138  0.0180  0.0237  0.0269  0.0282  0.0287  0.0278  0.0282  0.0276  0.0269  0.0269  0.0279  0.0285  0.0284  0.0282  0.0269  0.0237  0.0198  0.0138
 15  0.0476  0.0541  0.0628  0.0675  0.0724  0.0747  0.0765  0.0775  0.0774  0.0768  0.0772  0.0768  0.0759  0.0749  0.0724  0.0675  0.0628  0.0541  0.0476
 20  0.0793  0.0846  0.0829  0.0820  0.0897  0.0918  0.0921  0.0920  0.0896  0.0893  0.0903  0.0909  0.0914  0.0881  0.0869  0.0792  0.0801  0.0818  0.0765
 25  0.0828  0.0928  0.0920  0.0908  0.0919  0.0939  0.0939  0.0907  0.0883  0.0861  0.0872  0.0897  0.0911  0.0896  0.0893  0.0882  0.0894  0.0902  0.0802
 30  0.0401  0.0606  0.0642  0.0782  0.0845  0.0964  0.1000  0.1005  0.1008  0.0996  0.0985  0.0988  0.0969  0.0960  0.0938  0.0875  0.0735  0.0699  0.0494
 35  0.0380  0.0459  0.0604  0.0682  0.0828  0.0886  0.1027  0.1094  0.1106  0.1100  0.1098  0.1109  0.1087  0.1054  0.0980  0.0834  0.0756  0.0611  0.0532
 40  0.0558  0.0635  0.0588  0.0679  0.0820  0.0845  0.0948  0.0985  0.1021  0.1021  0.1033  0.0994  0.0933  0.0925  0.0882  0.0741  0.0650  0.0697  0.0620
 45  0.0750  0.0715  0.0746  0.0749  0.0837  0.0842  0.0826  0.0850  0.0896  0.0900  0.0893  0.0882  0.0858  0.0808  0.0798  0.0710  0.0707  0.0676  0.0711
 50  0.0851  0.0935  0.0968  0.0956  0.1018  0.1007  0.0953  0.0931  0.0962  0.1019  0.1024  0.1023  0.1032  0.0999  0.0995  0.0933  0.0945  0.0912  0.0828
 55  0.0768  0.0788  0.0701  0.0812  0.0979  0.0960  0.0939  0.0926  0.0943  0.0988  0.0919  0.0833  0.0853  0.0923  0.0985  0.0818  0.0707  0.0794  0.0774
 60  0.0677  0.0756  0.0788  0.0730  0.0762  0.0771  0.0825  0.0839  0.0851  0.0856  0.0850  0.0835  0.0837  0.0829  0.0808  0.0777  0.0834  0.0803  0.0723
 70  0.0416  0.0411  0.0416  0.0385  0.0804  0.0784  0.0928  0.0916  0.1072  0.1231  0.1121  0.1000  0.0956  0.0949  0.0926  0.0507  0.0538  0.0533  0.0538
 80  0.0316  0.0273  0.0247  0.0302  0.0327  0.0323  0.0329  0.0386  0.0389  0.0444  0.0405  0.0382  0.0405  0.0390  0.0385  0.0345  0.0290  0.0316  0.0359
 90  0.0330  0.0302  0.0294  0.0378  0.0408  0.0404  0.0411  0.0395  0.0411  0.0414  0.0405  0.0372  0.0367  0.0423  0.0399  0.0368  0.0285  0.0292  0.0320
                    </tableData>
                    <tableData breakPoint="25.0">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.1067 -0.1112 -0.1168 -0.1196 -0.1343 -0.1351 -0.1311 -0.1208 -0.1188 -0.1193 -0.1216 -0.1251 -0.1260 -0.1308 -0.1306 -0.1159 -0.1131 -0.1075 -0.1030
-15 -0.1151 -0.1216 -0.1278 -0.1366 -0.1465 -0.1505 -0.1518 -0.1528 -0.1559 -0.1568 -0.1566 -0.1541 -0.1517 -0.1558 -0.1503 -0.1404 -0.1316 -0.1254 -0.1189
-10 -0.1164 -0.1290 -0.1423 -0.1472 -0.1530 -0.1558 -0.1591 -0.1621 -0.1668 -0.1796 -0.1665 -0.1623 -0.1593 -0.1573 -0.1548 -0.1490 -0.1441 -0.1308 -0.1182
 -5 -0.1002 -0.1135 -0.1207 -0.1265 -0.1373 -0.1441 -0.1453 -0.1456 -0.1471 -0.1475 -0.1481 -0.1461 -0.1449 -0.1417 -0.1378 -0.1269 -0.1212 -0.1139 -0.1007
  0 -0.0925 -0.1016 -0.1093 -0.1141 -0.1156 -0.1181 -0.1203 -0.1212 -0.1225 -0.1222 -0.1219 -0.1208 -0.1190 -0.1168 -0.1146 -0.1130 -0.1082 -0.1005 -0.0914
  5 -0.0716 -0.0735 -0.0791 -0.0846 -0.0830 -0.0857 -0.0882 -0.0910 -0.0951 -0.0965 -0.0966 -0.0915 -0.0868 -0.0851 -0.0830 -0.0846 -0.0785 -0.0733 -0.0711
 10 -0.0319 -0.0358 -0.0378 -0.0424 -0.0408 -0.0445 -0.0489 -0.0544 -0.0587 -0.0543 -0.0554 -0.0533 -0.0480 -0.0435 -0.0421 -0.0436 -0.0391 -0.0352 -0.0331
 15  0.0049  0.0021  0.0022 -0.0012 -0.0015 -0.0036 -0.0075 -0.0067 -0.0022 -0.0003 -0.0073 -0.0104 -0.0096 -0.0066 -0.0033 -0.0031  0.0003  0.0003  0.0030
 20  0.0322  0.0474  0.0398  0.0294  0.0082  0.0022  0.0034  0.0001 -0.0067 -0.0087 -0.0107 -0.0006 -0.0097 -0.0112 -0.0166  0.0046  0.0150  0.0226  0.0074
 25  0.0557  0.0527  0.0444  0.0360  0.0118  0.0051 -0.0016 -0.0078 -0.0131 -0.0078 -0.0122 -0.0061 -0.0033 -0.0049 -0.0066  0.0176  0.0261  0.0344  0.0374
 30  0.0023  0.0119  0.0108  0.0036  0.0034  0.0129  0.0139  0.0119  0.0094  0.0092  0.0086  0.0092  0.0109  0.0146  0.0188  0.0190  0.0263  0.0273  0.0178
 35  0.0042  0.0112  0.0109  0.0032  0.0051  0.0070  0.0163  0.0183  0.0170  0.0198  0.0218  0.0215  0.0211  0.0194  0.0171  0.0153  0.0229  0.0232  0.0163
 40  0.0210  0.0286  0.0134  0.0121  0.0119  0.0165  0.0123  0.0135  0.0121  0.0135  0.0125  0.0151  0.0124  0.0142  0.0123  0.0126  0.0139  0.0291  0.0215
 45  0.0267  0.0248  0.0119  0.0081  0.0105  0.0135  0.0126  0.0086  0.0078  0.0108  0.0063  0.0084  0.0093  0.0100  0.0103  0.0078  0.0117  0.0246  0.0264
 50  0.0209  0.0303  0.0345  0.0266  0.0362  0.0340  0.0284  0.0237  0.0241  0.0270  0.0296  0.0314  0.0329  0.0312  0.0324  0.0321  0.0376  0.0315  0.0202
 55  0.0136  0.0215  0.0189  0.0299  0.0377  0.0332  0.0286  0.0258  0.0267  0.0305  0.0256  0.0191  0.0223  0.0301  0.0369  0.0268  0.0072  0.0154  0.0128
 60 -0.0062  0.0083  0.0178  0.0157  0.0332  0.0273  0.0257  0.0244  0.0271  0.0288  0.0279  0.0260  0.0262  0.0265  0.0243  0.0192  0.0223  0.0153  0.0048
 70 -0.0447 -0.0366 -0.0286 -0.0287  0.0300  0.0334  0.0531  0.0483  0.0547  0.0545  0.0591  0.0625  0.0625  0.0547  0.0445 -0.0183 -0.0215 -0.0246 -0.0167
 80 -0.0513 -0.0536 -0.0543 -0.0445 -0.0467 -0.0478 -0.0480 -0.0437 -0.0455 -0.0422 -0.0258  0.0152  0.0182 -0.0134 -0.0440 -0.0549 -0.0581 -0.0496 -0.0395
 90 -0.0472 -0.0542 -0.0593 -0.0492 -0.0406 -0.0417 -0.0390 -0.0440 -0.0431 -0.0432 -0.0424 -0.0438 -0.0433 -0.0377 -0.0400 -0.0496 -0.0597 -0.0504 -0.0393
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCx_lef">
            <description>
               Cx due to leading edge flaps coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <difference>
                    <table name="table/Cx_lef">
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/beta-deg</independentVar>
                        <tableData>
    -30     -25     -20  -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0277 -.0285 -.0318 -.0256 -.0184 -.0156 -.0159 -.0162 -.0174 -.0181 -.0179 -.0167 -.0168 -.0156 -.0153 -.0225 -.0287 -.0254 -.0246
-15 -.0314 -.0310 -.0259 -.0191 -.0161 -.0157 -.0162 -.0173 -.0189 -.0193 -.0186 -.0186 -.0170 -.0155 -.0154 -.0184 -.0252 -.0303 -.0307
-10 -.0295 -.0298 -.0260 -.0233 -.0209 -.0215 -.0214 -.0224 -.0230 -.0224 -.0220 -.0217 -.0213 -.0205 -.0199 -.0223 -.0250 -.0288 -.0285
-05 -.0148 -.0153 -.0163 -.0150 -.0167 -.0173 -.0185 -.0189 -.0193 -.0196 -.0192 -.0185 -.0179 -.0178 -.0162 -.0155 -.0168 -.0158 -.0153
 00 -.0136 -.0149 -.0143 -.0136 -.0168 -.0178 -.0182 -.0188 -.0197 -.0202 -.0196 -.0188 -.0180 -.0172 -.0160 -.0144 -.0151 -.0149 -.0144
 05 -.0029 -.0010 -.0003 -.0005 -.0004 -.0006 -.0017 -.0027 -.0033 -.0033 -.0033 -.0024 -.0014 -.0004 0.0004 0.0013 0.0011 -.0002 -.0021
 10 0.0085 0.0104 0.0116 0.0121 0.0131 0.0125 0.0122 0.0119 0.0104 0.0099 0.0096 0.0106 0.0117 0.0126 0.0127 0.0117 0.0112 0.0100 0.0081
 15 0.0145 0.0168 0.0196 0.0218 0.0225 0.0231 0.0238 0.0238 0.0231 0.0224 0.0224 0.0226 0.0227 0.0223 0.0222 0.0215 0.0193 0.0165 0.0142
 20 0.0165 0.0170 0.0205 0.0226 0.0252 0.0245 0.0236 0.0232 0.0233 0.0221 0.0232 0.0241 0.0250 0.0267 0.0276 0.0250 0.0229 0.0212 0.0189
 25 0.0138 0.0172 0.0157 0.0178 0.0226 0.0251 0.0264 0.0274 0.0271 0.0278 0.0275 0.0271 0.0267 0.0249 0.0252 0.0203 0.0183 0.0198 0.0164
 30 0.0092 0.0122 0.0129 0.0165 0.0202 0.0253 0.0279 0.0295 0.0296 0.0301 0.0309 0.0306 0.0278 0.0261 0.0247 0.0200 0.0174 0.0167 0.0137
 35 0.0099 0.0134 0.0162 0.0149 0.0208 0.0229 0.0273 0.0286 0.0303 0.0305 0.0286 0.0307 0.0292 0.0259 0.0253 0.0194 0.0207 0.0179 0.0144
 40 0.0206 0.0202 0.0236 0.0246 0.0289 0.0293 0.0290 0.0320 0.0317 0.0328 0.0314 0.0305 0.0289 0.0281 0.0262 0.0219 0.0209 0.0175 0.0179
 45 0.0257 0.0274 0.0266 0.0236 0.0266 0.0283 0.0236 0.0298 0.0268 0.0309 0.0307 0.0280 0.0238 0.0284 0.0254 0.0224 0.0254 0.0262 0.0245
                        </tableData>
                    </table>
                    <table name="table/Cx_dh0">
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/beta-deg</independentVar>
                        <tableData>
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.1072 -.1061 -.1129 -.1096 -.1084 -.1040 -.0978 -.0959 -.0932 -.0933 -.0956 -.0957 -.0962 -.0967 -.0992 -.1004 -.1037 -.0969 -.0980
-15 -.1006 -.1035 -.1025 -.0998 -.0966 -.0966 -.0960 -.0967 -.0974 -.0978 -.0975 -.0977 -.0972 -.0968 -.0974 -.1006 -.1033 -.1043 -.1014
-10 -.0853 -.0901 -.0903 -.0906 -.0896 -.0903 -.0907 -.0918 -.0929 -.0982 -.0930 -.0919 -.0912 -.0898 -.0904 -.0914 -.0911 -.0909 -.0861
-05 -.0546 -.0597 -.0637 -.0662 -.0727 -.0755 -.0767 -.0778 -.0780 -.0784 -.0776 -.0766 -.0750 -.0733 -.0703 -.0638 -.0613 -.0573 -.0522
 00 -.0355 -.0381 -.0404 -.0416 -.0450 -.0461 -.0469 -.0478 -.0485 -.0489 -.0483 -.0475 -.0467 -.0449 -.0433 -.0399 -.0387 -.0364 -.0338
 05 -.0012 0.0000 0.0010 0.0004 -.0036 -.0042 -.0049 -.0055 -.0071 -.0066 -.0072 -.0061 -.0050 -.0035 -.0027 0.0013 0.0019 0.0000 -.0021
 10 0.0359 0.0491 0.0458 0.0490 0.0503 0.0508 0.0499 0.0509 0.0497 0.0490 0.0490 0.0500 0.0506 0.0505 0.0503 0.0490 0.0458 0.0419 0.0359
 15 0.0780 0.0845 0.0932 0.0979 0.1028 0.1051 0.1069 0.1079 0.1078 0.1072 0.1076 0.1072 0.1063 0.1053 0.1028 0.0979 0.0932 0.0845 0.0780
 20 0.1183 0.1236 0.1219 0.1210 0.1287 0.1308 0.1311 0.1310 0.1286 0.1283 0.1293 0.1299 0.1304 0.1271 0.1259 0.1182 0.1191 0.1208 0.1155
 25 0.1267 0.1367 0.1359 0.1347 0.1358 0.1378 0.1378 0.1346 0.1322 0.1300 0.1311 0.1336 0.1350 0.1335 0.1332 0.1321 0.1333 0.1341 0.1241
 30 0.0941 0.1146 0.1182 0.1322 0.1385 0.1504 0.1540 0.1545 0.1548 0.1536 0.1525 0.1528 0.1509 0.1500 0.1478 0.1415 0.1275 0.1239 0.1034
 35 0.0885 0.0964 0.1109 0.1189 0.1333 0.1391 0.1532 0.1599 0.1611 0.1605 0.1603 0.1614 0.1592 0.1559 0.1485 0.1339 0.1261 0.1116 0.1037
 40 0.1089 0.1166 0.1119 0.1210 0.1351 0.1376 0.1479 0.1516 0.1552 0.1552 0.1564 0.1525 0.1464 0.1456 0.1413 0.1272 0.1181 0.1228 0.1151
 45 0.1232 0.1197 0.1228 0.1231 0.1319 0.1324 0.1308 0.1332 0.1378 0.1382 0.1375 0.1364 0.1340 0.1380 0.1280 0.1192 0.1189 0.1158 0.1193
 50 0.1135 0.1185 0.1184 0.1171 0.1243 0.1279 0.1279 0.1258 0.1257 0.1281 0.1258 0.1228 0.1221 0.1186 0.1180 0.1108 0.1121 0.1122 0.1072
 55 0.1137 0.1195 0.1146 0.1161 0.1209 0.1211 0.1211 0.1195 0.1183 0.1200 0.1185 0.1153 0.1160 0.1152 0.1135 0.1087 0.1072 0.1121 0.1063
 60 0.1037 0.1090 0.1094 0.1049 0.1109 0.1123 0.1181 0.1184 0.1170 0.1147 0.1141 0.1126 0.1129 0.1129 0.1109 0.1049 0.1094 0.1090 0.1037
 70 0.0857 0.0858 0.0857 0.0796 0.0851 0.0919 0.1150 0.1087 0.1089 0.1025 0.1022 0.1007 0.1012 0.0994 0.0952 0.0897 0.0958 0.0959 0.0958
 80 0.0842 0.0807 0.0787 0.0778 0.0791 0.0793 0.0805 0.0846 0.0808 0.0821 0.0802 0.0799 0.0826 0.0800 0.0709 0.0756 0.0765 0.0785 0.0820
 90 0.0847 0.0813 0.0798 0.0824 0.0843 0.0843 0.0853 0.0841 0.0858 0.0864 0.0857 0.0828 0.0817 0.0857 0.0816 0.0797 0.0771 0.0786 0.0820
                        </tableData>
                    </table>
                </difference>
            </product>
        </function>

        <!--<function name="aero/coefficient/dCx_sb">
            <description>
               Cx due speed brake coefficient.

               These values are wrong. Mistake in TP 1538.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>fcs/speedbrake-pos-norm</property>
                <table name="table/dCx_sb">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.0101
-15 -.0101
-10 -.0101
-05 -.0101
 00 -.0101
 05 -.0358
 10 -.0790
 15 -.1227
 20 -.1827
 25 -.1892
 30 -.1988
 35 -.2000
 40 -.1874
 45 -.1673
 50 -.1476
 55 -.1310
 60 -.1279
 70 -.1325
 80 -.1250
 90 -.1250
                     </tableData>
                </table>
            </product>
        </function>-->

        <function name="aero/coefficient/dCx_sb">
            <description>
               Cx due speed brake coefficient.

               Source: TN-D-8176
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <!--<property>metrics/Sw-sqft</property>--><v>280</v>
                <property>fcs/speedbrake-pos-norm</property>
                <table name="table/dCx_sb">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-10 -.0790
-05 -.0498
 00 -.0500
 05 -.0498
 10 -.0493
 15 -.0483
 20 -.0470
 25 -.0453
 30 -.0433
 35 -.0410
 40 -.0383
 45 -.0354
 50 -.0322
 55 -.0287
 60 -.0250
 70 -.0171
 80 -.0087
 90 0.0000
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/Cx_q">
            <description>
               Cx due to pitch rate coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>aero/ci2vel</property>
                <property>velocities/q-rad_sec</property>
                <table name="table/Cx_q">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .953
-15 .953
-10 .953
-05 1.55
 00 1.90
 05 2.46
 10 2.92
 15 3.30
 20 2.76
 25 2.05
 30 1.50
 35 1.49
 40 1.83
 45 1.21
 50 1.33
 55 1.61
 60 .910
 70 3.43
 80 .617
 90 .273
                    </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCx_q-lef">
            <description>
               Cx due to pitch rate due to leading edge flaps coefficient.

               Source for alpha 50+: TN-D-8176
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>aero/ci2vel</property>
                <property>velocities/q-rad_sec</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <table name="table/dCx_q-lef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -1.22
-15 -1.22
-10 -1.22
-05 -1.66
 00 -1.62
 05 -1.58
 10 -1.96
 15 -2.51
 20 -2.04
 25 -1.64
 30 -.824
 35 -.817
 40 -1.10
 45 -.550
 50 0.000
 55 0.000
 60 0.000
 70 0.000
 80 0.000
 90 0.000
                     </tableData>
                </table>
            </product>
        </function>        

    </axis>
















    <function name="aero/coefficient/CDz">
        <description>Drag</description>
        <product>             
            <sum>
                <property>aero/coefficient/CDgear</property>
                <property>aero/coefficient/CDtef</property>
                <property>aero/coefficient/CDwave</property>
            </sum>
            <sin>
              <property>aero/alpha-rad</property>
            </sin>
            <v>-1</v>
        </product>
    </function>  

    <function name="aero/coefficient/CLz">
        <description>Lift</description>
        <product>             
            <sum>
                <property>aero/coefficient/CLtef</property>
            </sum>
            <cos>
              <property>aero/alpha-rad</property>
            </cos>
            <v>-1</v>
        </product>
    </function>           

    <function name="aero/coefficient/Cz">
        <description>
           Cz coefficient
        </description>
        <product>
            <p>aero/coefficient/Cz_g</p>
            <table name="table/Cz">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <independentVar lookup="table">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                <tableData breakPoint="-25.0">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  1.2198  1.3050  1.3380  1.3913  1.4353  1.3835  1.3810  1.3533  1.3708  1.3648  1.3823  1.3750  1.3813  1.3795  1.3273  1.2575  1.2025  1.1575  1.1213
-15  1.0188  1.0865  1.1228  1.1563  1.1683  1.1713  1.1753  1.1910  1.2093  1.2240  1.2298  1.1865  1.1938  1.1740  1.1768  1.1675  1.1325  1.0888  1.0288
-10  0.8130  0.8603  0.8748  0.8923  0.9325  0.9363  0.9498  0.9645  0.9695  0.9833  0.9613  0.9380  0.9338  0.9238  0.9165  0.8663  0.8488  0.8413  0.7975
 -5  0.4463  0.4463  0.4575  0.4625  0.4918  0.5038  0.5160  0.5123  0.5213  0.5145  0.5035  0.4963  0.4888  0.4898  0.4850  0.4673  0.4435  0.4340  0.4420
  0  0.2265  0.2013  0.1813  0.1750  0.1853  0.1950  0.1995  0.1980  0.1955  0.2000  0.1995  0.1958  0.1910  0.1803  0.1823  0.1608  0.1805  0.1620  0.2003
  5 -0.0438 -0.0838 -0.1138 -0.1350 -0.1403 -0.1415 -0.1370 -0.1418 -0.1418 -0.1445 -0.1493 -0.1458 -0.1493 -0.1513 -0.1493 -0.1395 -0.1238 -0.0825 -0.0508
 10 -0.2875 -0.3513 -0.4075 -0.4463 -0.4590 -0.4658 -0.4733 -0.4835 -0.4808 -0.4750 -0.4775 -0.4698 -0.4640 -0.4673 -0.4600 -0.4413 -0.4090 -0.3460 -0.2853
 15 -0.5563 -0.6038 -0.6550 -0.7038 -0.7403 -0.7503 -0.7700 -0.7835 -0.7860 -0.7920 -0.7895 -0.7918 -0.7923 -0.7705 -0.7630 -0.7380 -0.6728 -0.5990 -0.5425
 20 -0.8088 -0.8875 -0.9488 -1.0150 -1.0578 -1.0700 -1.0810 -1.0848 -1.0895 -1.1068 -1.0868 -1.0838 -1.0818 -1.0698 -1.0658 -1.0123 -0.9248 -0.8763 -0.8130
 25 -1.1188 -1.1838 -1.2413 -1.3000 -1.3510 -1.3475 -1.3738 -1.3875 -1.3928 -1.3930 -1.4000 -1.3968 -1.4050 -1.3885 -1.3610 -1.3025 -1.2318 -1.1608 -1.1170
 30 -1.2638 -1.3213 -1.3788 -1.4413 -1.4988 -1.5945 -1.6220 -1.6410 -1.6483 -1.6443 -1.6485 -1.6360 -1.6098 -1.5973 -1.5790 -1.5030 -1.3965 -1.4160 -1.3488
 35 -1.5113 -1.5463 -1.6013 -1.6663 -1.7355 -1.7543 -1.7595 -1.8185 -1.8420 -1.8363 -1.8398 -1.8198 -1.8203 -1.7703 -1.7240 -1.6508 -1.5758 -1.5475 -1.4980
 40 -1.5713 -1.6300 -1.6763 -1.7463 -1.8168 -1.8380 -1.8135 -1.9013 -1.9415 -1.9643 -1.8263 -1.9298 -1.9223 -1.7248 -1.8398 -1.7750 -1.6960 -1.6238 -1.6008
 45 -1.5438 -1.6263 -1.6600 -1.6875 -1.7730 -1.9208 -1.9888 -1.8578 -1.9143 -1.9035 -1.9368 -1.9625 -1.8165 -1.8250 -1.8688 -1.8495 -1.7795 -1.6993 -1.6533
 50 -1.2325 -1.4163 -1.5250 -1.6375 -1.8088 -1.8415 -1.8193 -1.7680 -1.7843 -1.8673 -1.9120 -1.9488 -1.9683 -1.8815 -1.9428 -1.8103 -1.6760 -1.5668 -1.3965
 55 -1.6875 -1.7688 -1.7888 -1.7988 -1.8785 -1.9028 -1.9593 -1.9460 -1.9123 -1.9495 -1.8975 -1.7725 -1.8233 -1.8688 -1.9183 -1.6875 -1.6300 -1.6498 -1.5725
 60 -1.6500 -1.6913 -1.6725 -1.8700 -1.8843 -1.8223 -1.8405 -1.8268 -1.8198 -1.8430 -1.8725 -1.8228 -1.8835 -1.9025 -1.8653 -1.7275 -1.6910 -1.6970 -1.6410
 70 -1.6300 -1.6888 -1.6838 -1.8075 -1.7840 -1.8248 -1.9648 -1.8975 -1.8763 -1.9128 -1.8600 -1.7885 -1.8880 -1.9088 -1.8505 -1.7575 -1.8123 -1.7620 -1.7578
 80 -1.9188 -1.9263 -1.9125 -1.8800 -1.8288 -1.7990 -1.8730 -1.9133 -1.7845 -1.7690 -1.7915 -1.7113 -1.8065 -1.8180 -1.7378 -1.7625 -1.8215 -1.8483 -1.8030
 90 -1.9600 -1.9313 -1.8375 -1.8350 -1.9263 -2.0055 -1.9883 -1.9308 -1.9513 -1.9375 -1.9188 -1.9183 -1.9273 -2.0178 -1.9443 -1.8503 -1.8530 -1.9393 -1.9475
                </tableData>
                <tableData breakPoint="-10.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  1.1635  1.2325  1.2793  1.3138  1.3490  1.3035  1.2898  1.2670  1.2620  1.2560  1.2835  1.2813  1.2913  1.2883  1.2548  1.2088  1.1638  1.1188  1.0750
-15  0.9588  1.0090  1.0365  1.0638  1.0620  1.0600  1.0578  1.0648  1.0743  1.0840  1.0910  1.0690  1.0725  1.0603  1.0718  1.0688  1.0463  1.0125  0.9663
-10  0.7655  0.7928  0.7948  0.8073  0.8250  0.8240  0.8298  0.8333  0.8408  0.8458  0.8400  0.8293  0.8275  0.8225  0.8190  0.7925  0.7838  0.7788  0.7563
 -5  0.3338  0.3338  0.3413  0.3463  0.3655  0.3800  0.3860  0.3873  0.3750  0.3733  0.3685  0.3650  0.3588  0.3535  0.3450  0.3335  0.3235  0.3103  0.3208
  0  0.1090  0.0838  0.0638  0.0613  0.0740  0.0788  0.0845  0.0843  0.0830  0.0863  0.0845  0.0833  0.0798  0.0740  0.0673  0.0558  0.0705  0.0633  0.0965
  5 -0.1713 -0.2113 -0.2413 -0.2588 -0.2603 -0.2640 -0.2608 -0.2668 -0.2668 -0.2670 -0.2693 -0.2708 -0.2693 -0.2713 -0.2730 -0.2708 -0.2538 -0.2213 -0.1833
 10 -0.4313 -0.4975 -0.5513 -0.5875 -0.6003 -0.6083 -0.6170 -0.6235 -0.6258 -0.6250 -0.6263 -0.6210 -0.6165 -0.6135 -0.6100 -0.5963 -0.5615 -0.4985 -0.4378
 15 -0.6863 -0.7525 -0.8125 -0.8638 -0.8990 -0.9140 -0.9325 -0.9423 -0.9435 -0.9470 -0.9470 -0.9455 -0.9448 -0.9293 -0.9180 -0.8905 -0.8303 -0.7565 -0.6863
 20 -0.9775 -1.0600 -1.1313 -1.1938 -1.2340 -1.2538 -1.2685 -1.2748 -1.2720 -1.2780 -1.2630 -1.2600 -1.2580 -1.2498 -1.2370 -1.1910 -1.1148 -1.0600 -0.9780
 25 -1.2975 -1.3625 -1.4288 -1.4925 -1.5435 -1.5488 -1.5663 -1.5738 -1.5790 -1.5780 -1.5813 -1.5793 -1.5800 -1.5685 -1.5498 -1.4888 -1.4280 -1.3570 -1.2920
 30 -1.3925 -1.4688 -1.5450 -1.6263 -1.7050 -1.7870 -1.8108 -1.8248 -1.8258 -1.8268 -1.8273 -1.8198 -1.7998 -1.7798 -1.7590 -1.6968 -1.5665 -1.5335 -1.4500
 35 -1.5388 -1.6200 -1.7063 -1.8025 -1.8993 -1.9530 -2.0033 -2.0373 -2.0533 -2.0625 -2.0548 -2.0473 -2.0403 -2.0053 -1.9603 -1.8695 -1.7758 -1.6800 -1.6005
 40 -1.6600 -1.7525 -1.8413 -1.9425 -2.0455 -2.0505 -2.1135 -2.1525 -2.1703 -2.1880 -2.1513 -2.1848 -2.0660 -2.0673 -2.0810 -1.9713 -1.8773 -1.7688 -1.6908
 45 -1.6125 -1.5788 -1.7663 -1.9538 -2.1180 -2.2033 -2.1775 -2.2040 -2.2930 -2.2510 -2.2918 -2.2925 -2.2278 -2.2213 -2.1988 -2.1120 -1.8633 -1.6555 -1.6945
 50 -1.3650 -1.5563 -1.6700 -1.9175 -1.9913 -2.0378 -2.0293 -1.9768 -1.9743 -2.0398 -2.0695 -2.0913 -2.1083 -2.0315 -2.1015 -2.0315 -1.7773 -1.6568 -1.4740
 55 -1.6663 -1.6975 -1.6588 -1.7475 -1.9735 -2.0140 -2.0843 -2.0723 -2.0235 -2.0470 -2.0250 -1.9288 -1.9745 -1.9825 -1.9933 -1.7688 -1.6738 -1.7035 -1.6363
 60 -1.6800 -1.7575 -1.7600 -1.6963 -1.9043 -1.8760 -1.9255 -1.9418 -1.9610 -2.0118 -1.9788 -1.8690 -1.9123 -1.9600 -1.9528 -1.7425 -1.7985 -1.7958 -1.7310
 70 -1.6963 -1.7063 -1.7788 -1.7463 -1.8165 -1.8660 -1.9648 -1.9588 -1.9525 -2.0003 -1.9075 -1.7910 -1.8793 -1.9600 -1.8855 -1.8363 -1.8623 -1.8083 -1.8003
 80 -1.9188 -1.9800 -1.9550 -1.9688 -1.8988 -1.8478 -1.9018 -1.9533 -1.8670 -1.8940 -1.9178 -1.8375 -1.9253 -1.9293 -1.8303 -1.8888 -1.8653 -1.8833 -1.8293
 90 -1.9975 -2.0238 -1.9625 -1.9713 -1.9925 -2.0668 -1.9958 -1.9795 -1.9875 -1.9625 -1.9600 -1.9783 -2.0198 -2.0853 -1.9855 -1.9515 -1.9243 -1.9855 -1.9688
                 </tableData>
                <tableData breakPoint="0.0">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 1.0910 1.1400 1.2030 1.2150 1.2390 1.2010 1.1710 1.1570 1.1220 1.1160 1.1560 1.1600 1.1750 1.1720 1.1610 1.1450 1.1150 1.0700 1.0150
-15 0.9050 0.9390 0.9590 0.9800 0.9670 0.9600 0.9540 0.9510 0.9530 0.9590 0.9660 0.9640 0.9650 0.9590 0.9780 0.9800 0.9700 0.9450 0.9100
-10 0.7130 0.7190 0.7060 0.7110 0.7050 0.6990 0.6960 0.6870 0.6970 0.6920 0.7050 0.7080 0.7100 0.7100 0.7090 0.7100 0.7100 0.7100 0.7100
-05 0.2650 0.2650 0.2700 0.2750 0.2880 0.3050 0.3060 0.3110 0.2850 0.2870 0.2860 0.2850 0.2800 0.2710 0.2600 0.2510 0.2510 0.2340 0.2470
 00 -0.006 -0.030 -0.050 -0.050 -0.036 -0.035 -0.028 -0.027 -0.027 -0.025 -0.028 -0.028 -0.029 -0.031 -0.034 -0.048 -0.037 -0.033 -0.006
 05 -0.275 -0.315 -0.345 -0.360 -0.359 -0.364 -0.362 -0.368 -0.368 -0.367 -0.368 -0.372 -0.368 -0.370 -0.373 -0.377 -0.360 -0.335 -0.292
 10 -0.550 -0.620 -0.670 -0.705 -0.719 -0.727 -0.737 -0.741 -0.747 -0.750 -0.750 -0.746 -0.744 -0.736 -0.735 -0.725 -0.689 -0.626 -0.564
 15 -0.825 -0.910 -0.980 -1.035 -1.069 -1.089 -1.105 -1.111 -1.111 -1.112 -1.112 -1.108 -1.106 -1.098 -1.083 -1.053 -0.999 -0.924 -0.840
 20 -1.115 -1.200 -1.280 -1.340 -1.379 -1.405 -1.421 -1.431 -1.422 -1.418 -1.408 -1.405 -1.403 -1.396 -1.382 -1.336 -1.271 -1.210 -1.113
 25 -1.375 -1.440 -1.510 -1.575 -1.626 -1.635 -1.650 -1.655 -1.659 -1.658 -1.660 -1.658 -1.655 -1.646 -1.631 -1.570 -1.513 -1.442 -1.367
 30 -1.520 -1.615 -1.710 -1.810 -1.910 -1.977 -1.997 -2.006 -2.002 -2.008 -2.006 -2.001 -1.981 -1.961 -1.939 -1.888 -1.799 -1.651 -1.550
 35 -1.555 -1.665 -1.770 -1.885 -1.998 -2.073 -2.152 -2.171 -2.182 -2.200 -2.186 -2.186 -2.174 -2.149 -2.104 -2.002 -1.897 -1.760 -1.663
 40 -1.715 -1.830 -1.945 -2.065 -2.188 -2.183 -2.301 -2.310 -2.314 -2.328 -2.355 -2.231 -2.156 -2.281 -2.231 -2.095 -1.991 -1.860 -1.747
 45 -1.625 -1.570 -1.785 -2.000 -2.178 -2.272 -2.210 -2.264 -2.358 -2.311 -2.353 -2.350 -2.299 -2.290 -2.255 -2.157 -2.002 -1.648 -1.702
 50 -1.570 -1.735 -1.900 -2.050 -2.165 -2.254 -2.288 -2.258 -2.258 -2.326 -2.312 -2.290 -2.277 -2.184 -2.239 -2.109 -1.986 -1.848 -1.649
 55 -1.775 -1.900 -1.970 -2.055 -2.176 -2.184 -2.223 -2.211 -2.196 -2.252 -2.235 -2.145 -2.182 -2.165 -2.152 -2.025 -1.965 -1.931 -1.800
 60 -1.900 -1.935 -1.960 -1.995 -2.128 -2.111 -2.173 -2.183 -2.181 -2.208 -2.190 -2.094 -2.131 -2.150 -2.114 -1.990 -1.986 -1.962 -1.876
 70 -1.930 -1.945 -1.940 -1.920 -1.929 -2.021 -2.161 -2.160 -2.120 -2.134 -2.085 -2.011 -2.108 -2.125 -2.063 -1.970 -2.016 -1.947 -1.924
 80 -2.000 -2.045 -2.075 -2.080 -2.045 -1.994 -2.048 -2.092 -1.992 -2.004 -2.019 -1.930 -2.014 -2.018 -1.919 -2.000 -2.034 -2.032 -1.958
 90 -1.960 -1.950 -1.900 -2.010 -2.060 -2.158 -2.112 -2.117 -2.145 -2.140 -2.110 -2.107 -2.101 -2.169 -2.073 -2.074 -2.038 -2.088 -2.060
                </tableData>
                <tableData breakPoint="10.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  1.0035  1.0475  1.0943  1.1038  1.1140  1.0848  1.0860  1.0483  1.0208  1.0198  1.0498  1.0550  1.0675  1.0645  1.0573  1.0513  1.0288  0.9913  0.9425
-15  0.7925  0.8128  0.8178  0.8338  0.8258  0.8200  0.8165  0.8135  0.8193  0.8215  0.8285  0.8240  0.8250  0.8203  0.8343  0.8338  0.8275  0.8150  0.7975
-10  0.5993  0.5928  0.5773  0.5835  0.5813  0.5778  0.5748  0.5683  0.5758  0.5720  0.5800  0.5818  0.5838  0.5838  0.5840  0.5813  0.5813  0.5863  0.5963
 -5  0.1600  0.1538  0.1563  0.1613  0.1755  0.1888  0.1898  0.1910  0.1813  0.1845  0.1810  0.1763  0.1700  0.1610  0.1600  0.1435  0.1410  0.1353  0.1495
  0 -0.0848 -0.1175 -0.1438 -0.1513 -0.1435 -0.1413 -0.1355 -0.1333 -0.1370 -0.1363 -0.1393 -0.1393 -0.1440 -0.1460 -0.1490 -0.1555 -0.1433 -0.1280 -0.0923
  5 -0.3550 -0.4213 -0.4688 -0.5025 -0.5103 -0.5090 -0.5108 -0.5155 -0.5168 -0.5208 -0.5205 -0.5370 -0.5280 -0.5213 -0.5230 -0.5095 -0.4825 -0.4313 -0.3695
 10 -0.5938 -0.6325 -0.7263 -0.7838 -0.8278 -0.8308 -0.8458 -0.8560 -0.8683 -0.8738 -0.8763 -0.8660 -0.8715 -0.8548 -0.8475 -0.8200 -0.7678 -0.6885 -0.6028
 15 -0.8475 -0.9563 -1.0438 -1.1125 -1.1490 -1.1615 -1.1825 -1.1910 -1.1998 -1.1933 -1.1858 -1.1930 -1.1923 -1.1893 -1.1768 -1.1368 -1.0590 -0.9615 -0.8700
 20 -1.1013 -1.2000 -1.2888 -1.3600 -1.4103 -1.4375 -1.4523 -1.4585 -1.4508 -1.4480 -1.4418 -1.4363 -1.4418 -1.4360 -1.4220 -1.3623 -1.2898 -1.2163 -1.1093
 25 -1.3588 -1.4625 -1.5725 -1.6750 -1.7698 -1.8050 -1.8013 -1.8138 -1.8278 -1.8218 -1.8188 -1.8243 -1.8050 -1.8073 -1.7923 -1.6650 -1.5993 -1.4808 -1.3708
 30 -1.5200 -1.6338 -1.7475 -1.8650 -1.9825 -2.0520 -2.0883 -2.0998 -2.1033 -2.1005 -2.0985 -2.0873 -2.0723 -2.0585 -2.0353 -1.9393 -1.7878 -1.6785 -1.5663
 35 -1.7238 -1.9038 -2.0650 -2.1988 -2.3155 -2.3005 -2.2870 -2.3648 -2.3508 -2.3350 -2.3973 -2.3798 -2.3340 -2.2865 -2.2478 -2.1008 -1.9483 -1.7600 -1.6830
 40 -1.8825 -1.9788 -2.0813 -2.1950 -2.3155 -2.4055 -2.3535 -2.3913 -2.2765 -2.4318 -2.4350 -2.4448 -2.3923 -2.3460 -2.3210 -2.1800 -2.0835 -1.9988 -1.9108
 45 -1.5813 -1.4625 -1.7300 -2.0000 -2.1968 -2.2808 -2.1800 -2.2615 -2.4043 -2.3048 -2.3780 -2.3738 -2.2940 -2.2938 -2.2638 -2.1795 -1.9908 -1.5318 -1.6508
 50 -1.7413 -1.9300 -2.0413 -2.3063 -2.1350 -2.1865 -2.1830 -2.1418 -2.1593 -2.2448 -2.2758 -2.2788 -2.2983 -2.1815 -2.2128 -2.1953 -1.9235 -1.8055 -1.6253
 55 -1.7250 -1.8225 -1.8125 -1.8663 -2.1223 -2.1528 -2.2155 -2.2085 -2.1810 -2.2258 -2.1738 -2.0488 -2.0983 -2.1400 -2.1870 -1.9325 -1.8725 -1.8735 -1.7775
 60 -1.7738 -1.8775 -1.9063 -1.9288 -2.0893 -2.0535 -2.0968 -2.1080 -2.1298 -2.1793 -2.1575 -2.0578 -2.1010 -2.1400 -2.1228 -1.9600 -1.9298 -1.9008 -1.8098
 70 -1.7088 -1.7038 -1.7613 -1.7438 -2.0015 -2.0548 -2.1560 -2.1463 -2.0300 -2.3015 -2.2013 -2.0773 -2.1505 -2.1700 -2.1118 -1.8750 -1.8860 -1.8470 -1.8540
 80 -2.0838 -2.1425 -2.1150 -2.1613 -2.0550 -1.8903 -1.9555 -2.0070 -1.9095 -1.9240 -1.9540 -1.8813 -1.9690 -1.9655 -1.8603 -1.9550 -1.8990 -1.9195 -1.8680
 90 -2.0200 -2.0375 -1.9688 -2.0925 -2.0175 -2.1055 -2.0483 -2.0420 -2.0550 -2.0363 -2.0150 -2.0145 -2.0123 -2.0765 -1.9768 -2.0390 -1.8968 -1.9655 -1.9575
                </tableData>
                <tableData breakPoint="25.0">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  0.6310  0.6525  0.6293  0.6263  0.5790  0.5860  0.5785  0.5820  0.5895  0.6085  0.5910  0.6038  0.6063  0.6083  0.6110  0.6513  0.6588  0.6575  0.6338
-15  0.4138  0.3840  0.3365  0.3363  0.3458  0.3475  0.3503  0.3460  0.3655  0.3553  0.3598  0.3490  0.3525  0.3515  0.3468  0.3363  0.3450  0.3763  0.4163
-10  0.1330  0.0853  0.0560  0.0660  0.0775  0.0815  0.0785  0.0820  0.0845  0.0833  0.0738  0.0655  0.0700  0.0700  0.0740  0.0537  0.0600  0.0850  0.1350
 -5  0.0588  0.0463  0.0450  0.0500  0.0668  0.0763  0.0760  0.0748  0.0800  0.0845  0.0798  0.0713  0.0638  0.0535  0.0613  0.0385  0.0335  0.0378  0.0545
  0 -0.1860 -0.2300 -0.2625 -0.2813 -0.2810 -0.2713 -0.2730 -0.2695 -0.2770 -0.2788 -0.2818 -0.2830 -0.2915 -0.2935 -0.2965 -0.2930 -0.2808 -0.2505 -0.2035
  5 -0.4125 -0.4963 -0.5575 -0.6038 -0.6178 -0.6128 -0.6170 -0.6218 -0.6230 -0.6308 -0.6305 -0.6558 -0.6430 -0.6288 -0.6305 -0.6045 -0.5700 -0.5000 -0.4245
 10 -0.6375 -0.7075 -0.7825 -0.8613 -0.9353 -0.9320 -0.9533 -0.9698 -0.9870 -0.9950 -0.9988 -0.9835 -0.9953 -0.9710 -0.9575 -0.9138 -0.8440 -0.7485 -0.6415
 15 -0.8750 -1.0100 -1.1175 -1.2038 -1.2428 -1.2465 -1.2725 -1.2848 -1.3085 -1.2883 -1.2720 -1.2918 -1.2923 -1.2968 -1.2855 -1.2343 -1.1290 -1.0065 -0.9038
 20 -1.0400 -1.1938 -1.3300 -1.4525 -1.5540 -1.5863 -1.5998 -1.5898 -1.5883 -1.5880 -1.6018 -1.5850 -1.6205 -1.6235 -1.6083 -1.4823 -1.3798 -1.2488 -1.0930
 25 -1.3563 -1.4650 -1.5850 -1.6938 -1.7973 -1.8375 -1.8300 -1.8438 -1.8603 -1.8530 -1.8488 -1.8555 -1.8338 -1.8385 -1.8235 -1.6838 -1.6155 -1.4883 -1.3720
 30 -1.5200 -1.6400 -1.7600 -1.8850 -2.0088 -2.0783 -2.1195 -2.1323 -2.1395 -2.1330 -2.1310 -2.1173 -2.1035 -2.0923 -2.0690 -1.9568 -1.8053 -1.6885 -1.5725
 35 -1.6300 -1.7713 -1.9013 -2.0225 -2.1393 -2.1630 -2.2120 -2.2573 -2.2570 -2.2600 -2.2798 -2.2723 -2.2453 -2.2103 -2.1678 -2.0458 -1.9195 -1.7600 -1.6718
 40 -1.7900 -1.8863 -1.9888 -2.1025 -2.2230 -2.3130 -2.2610 -2.2988 -2.1840 -2.3393 -2.3425 -2.3523 -2.2998 -2.2535 -2.2285 -2.0875 -1.9910 -1.9063 -1.8183
 45 -1.7688 -1.9138 -1.9600 -2.0000 -2.1180 -2.2458 -2.3050 -2.2715 -2.2093 -2.3310 -2.2730 -2.2725 -2.3153 -2.2800 -2.2263 -2.0845 -2.0370 -2.0193 -1.8670
 50 -1.5700 -1.7413 -1.9000 -2.0500 -2.1538 -2.2065 -2.1818 -2.1330 -2.1543 -2.2448 -2.2545 -2.2550 -2.2495 -2.1453 -2.1915 -2.1103 -1.9835 -1.8393 -1.6340
 55 -1.6813 -1.7875 -1.8575 -1.9238 -2.0098 -2.1665 -2.1743 -2.0860 -2.2060 -2.2258 -2.1950 -2.0913 -2.1233 -2.1750 -2.0958 -1.9313 -1.8738 -1.8635 -1.7563
 60 -1.7688 -1.8850 -1.9600 -2.0263 -2.1093 -2.0898 -2.1118 -2.1093 -2.1223 -2.1655 -2.1738 -2.1053 -2.1585 -2.1825 -2.1515 -2.0025 -1.9535 -1.9220 -1.8285
 70 -1.7425 -1.7450 -1.7525 -1.7825 -1.8590 -1.9235 -2.0335 -2.3025 -1.9700 -2.2903 -2.2425 -1.8535 -2.2493 -2.2338 -2.1405 -1.9700 -1.8798 -1.8658 -1.8615
 80 -1.9375 -1.9638 -1.9563 -1.9300 -1.8775 -1.8528 -1.9318 -1.9833 -1.8695 -1.8728 -2.0065 -2.0350 -2.1228 -2.0130 -1.8015 -1.8000 -1.8653 -1.8945 -1.8518
 90 -1.9163 -1.9125 -1.8625 -1.8538 -1.9463 -2.0493 -2.0083 -2.0195 -2.0513 -2.0513 -2.0050 -1.9795 -1.9748 -2.0640 -1.9905 -1.9003 -1.9255 -1.9643 -1.9238
                 </tableData>
            </table>
        </product>
    </function>

    <function name="aero/coefficient/dCz_lef">
        <description>
           Cz due to leading edge flaps coefficient.
        </description>
        <product>
            <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
            <difference>
            <table name="table/Cz_lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData>
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 1.1830 1.2460 1.2790 1.2900 1.3690 1.3640 1.2970 1.2770 1.2760 1.2560 1.2810 1.2800 1.3120 1.3150 1.3060 1.2270 1.2160 1.1830 1.1200
-15 0.9600 1.0180 1.0550 1.0930 1.0580 1.0390 1.0310 1.0190 1.0250 1.0350 1.0330 1.0420 1.0430 1.0560 1.0560 1.0910 1.0530 1.0160 0.9580
-10 0.7090 0.7100 0.7020 0.7040 0.7010 0.7100 0.7300 0.7290 0.7290 0.7250 0.7290 0.7280 0.7280 0.7230 0.7110 0.7140 0.7120 0.7200 0.7190
-05 0.2220 0.2160 0.2310 0.2270 0.2400 0.2430 0.2440 0.2490 0.2490 0.2480 0.2480 0.2420 0.2390 0.2350 0.2290 0.2160 0.2200 0.2050 0.2110
 00 -.0660 -.0840 -.0900 -.1050 -.1040 -.0990 -.1070 -.0990 -.0990 -.1000 -.1010 -.1040 -.1040 -.1040 -.1060 -.1070 -.0920 -.0860 -.0680
 05 -.3170 -.3470 -.3900 -.4140 -.4200 -.4170 -.4170 -.4210 -.4240 -.4280 -.4210 -.4280 -.4220 -.4230 -.4250 -.4190 -.3950 -.5320 -.3220
 10 -.5690 -.6190 -.6790 -.7030 -.7280 -.7650 -.7720 -.7740 -.7720 -.7740 -.7700 -.7670 -.7610 -.7540 -.7560 -.7310 -.7070 -.6450 -.5970
 15 -0.853 -0.929 -1.018 -1.070 -1.098 -1.116 -1.114 -1.151 -1.142 -1.139 -1.135 -1.118 -1.112 -1.107 -1.099 -1.071 -1.019 -0.930 -0.854
 20 -1.106 -1.168 -1.228 -1.314 -1.348 -1.359 -1.362 -1.352 -1.357 -1.355 -1.371 -1.376 -1.370 -1.379 -1.399 -1.365 -1.279 -1.219 -1.157
 25 -1.314 -1.407 -1.465 -1.506 -1.564 -1.598 -1.628 -1.647 -1.646 -1.650 -1.642 -1.641 -1.618 -1.599 -1.585 -1.527 -1.486 -1.428 -1.335
 30 -1.496 -1.510 -1.589 -1.692 -1.775 -1.814 -1.846 -1.875 -1.879 -1.883 -1.891 -1.876 -1.843 -1.838 -1.811 -1.729 -1.625 -1.546 -1.532
 35 -1.594 -1.694 -1.807 -1.875 -1.957 -1.976 -2.032 -2.060 -2.070 -2.077 -2.038 -2.039 -2.028 -2.005 -1.986 -1.904 -1.836 -1.713 -1.623
 40 -1.683 -1.755 -1.912 -1.999 -2.111 -2.149 -2.147 -2.204 -2.207 -2.204 -2.205 -2.195 -2.193 -2.174 -2.133 -2.021 -1.934 -1.777 -1.705
 45 -1.664 -1.783 -1.859 -1.962 -2.030 -2.129 -1.917 -2.143 -2.050 -2.208 -2.201 -2.182 -2.077 -2.209 -2.126 -2.058 -1.955 -1.879 -1.790
                 </tableData>
            </table>
            <table name="table/Cz_dh0">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData>
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 1.0910 1.1400 1.2030 1.2150 1.2390 1.2010 1.1710 1.1570 1.1220 1.1160 1.1560 1.1600 1.1750 1.1720 1.1610 1.1450 1.1150 1.0700 1.0150
-15 0.9050 0.9390 0.9590 0.9800 0.9670 0.9600 0.9540 0.9510 0.9530 0.9590 0.9660 0.9640 0.9650 0.9590 0.9780 0.9800 0.9700 0.9450 0.9100
-10 0.7130 0.7190 0.7060 0.7110 0.7050 0.6990 0.6960 0.6870 0.6970 0.6920 0.7050 0.7080 0.7100 0.7100 0.7090 0.7100 0.7100 0.7100 0.7100
-05 0.2650 0.2650 0.2700 0.2750 0.2880 0.3050 0.3060 0.3110 0.2850 0.2870 0.2860 0.2850 0.2800 0.2710 0.2600 0.2510 0.2510 0.2340 0.2470
 00 -0.006 -0.030 -0.050 -0.050 -0.036 -0.035 -0.028 -0.027 -0.027 -0.025 -0.028 -0.028 -0.029 -0.031 -0.034 -0.048 -0.037 -0.033 -0.006
 05 -0.275 -0.315 -0.345 -0.360 -0.359 -0.364 -0.362 -0.368 -0.368 -0.367 -0.368 -0.372 -0.368 -0.370 -0.373 -0.377 -0.360 -0.335 -0.292
 10 -0.550 -0.620 -0.670 -0.705 -0.719 -0.727 -0.737 -0.741 -0.747 -0.750 -0.750 -0.746 -0.744 -0.736 -0.735 -0.725 -0.689 -0.626 -0.564
 15 -0.825 -0.910 -0.980 -1.035 -1.069 -1.089 -1.105 -1.111 -1.111 -1.112 -1.112 -1.108 -1.106 -1.098 -1.083 -1.053 -0.999 -0.924 -0.840
 20 -1.115 -1.200 -1.280 -1.340 -1.379 -1.405 -1.421 -1.431 -1.422 -1.418 -1.408 -1.405 -1.403 -1.396 -1.382 -1.336 -1.271 -1.210 -1.113
 25 -1.375 -1.440 -1.510 -1.575 -1.626 -1.635 -1.650 -1.655 -1.659 -1.658 -1.660 -1.658 -1.655 -1.646 -1.631 -1.570 -1.513 -1.442 -1.367
 30 -1.520 -1.615 -1.710 -1.810 -1.910 -1.977 -1.997 -2.006 -2.002 -2.008 -2.006 -2.001 -1.981 -1.961 -1.939 -1.888 -1.799 -1.651 -1.550
 35 -1.555 -1.665 -1.770 -1.885 -1.998 -2.073 -2.152 -2.171 -2.182 -2.200 -2.186 -2.186 -2.174 -2.149 -2.104 -2.002 -1.897 -1.760 -1.663
 40 -1.715 -1.830 -1.945 -2.065 -2.188 -2.183 -2.301 -2.310 -2.314 -2.328 -2.355 -2.231 -2.156 -2.281 -2.231 -2.095 -1.991 -1.860 -1.747
 45 -1.625 -1.570 -1.785 -2.000 -2.178 -2.272 -2.210 -2.264 -2.358 -2.311 -2.353 -2.350 -2.299 -2.290 -2.255 -2.157 -2.002 -1.648 -1.702
 50 -1.570 -1.735 -1.900 -2.050 -2.165 -2.254 -2.288 -2.258 -2.258 -2.326 -2.312 -2.290 -2.277 -2.184 -2.239 -2.109 -1.986 -1.848 -1.649
 55 -1.775 -1.900 -1.970 -2.055 -2.176 -2.184 -2.223 -2.211 -2.196 -2.252 -2.235 -2.145 -2.182 -2.165 -2.152 -2.025 -1.965 -1.931 -1.800
 60 -1.900 -1.935 -1.960 -1.995 -2.128 -2.111 -2.173 -2.183 -2.181 -2.208 -2.190 -2.094 -2.131 -2.150 -2.114 -1.990 -1.986 -1.962 -1.876
 70 -1.930 -1.945 -1.940 -1.920 -1.929 -2.021 -2.161 -2.160 -2.120 -2.134 -2.085 -2.011 -2.108 -2.125 -2.063 -1.970 -2.016 -1.947 -1.924
 80 -2.000 -2.045 -2.075 -2.080 -2.045 -1.994 -2.048 -2.092 -1.992 -2.004 -2.019 -1.930 -2.014 -2.018 -1.919 -2.000 -2.034 -2.032 -1.958
 90 -1.960 -1.950 -1.900 -2.010 -2.060 -2.158 -2.112 -2.117 -2.145 -2.140 -2.110 -2.107 -2.101 -2.169 -2.073 -2.074 -2.038 -2.088 -2.060
                </tableData>
            </table>
        </difference>
        </product>
    </function>

    <!--<function name="aero/coefficient/dCz_sb">
        <description>
           Cz due speed brake coefficient.

           TP 1538 is unreliable in this regard, these numbers makes no sense.
        </description>
        <product>
            <property>fcs/speedbrake-pos-norm</property>
            <table name="table/dCz_sb">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 -.3858
-15 -.3858
-10 -.3858
-05 -.3858
 00 -.3858
 05 -.2685
 10 -.3021
 15 -.4248
 20 -.2094
 25 -.0969
 30 0.0438
 35 0.0947
 40 0.0014
 45 -.0097
 50 -.0153
 55 -.0520
 60 -.0010
 70 -.0202
 80 -.0369
 90 -.0369
                 </tableData>
            </table>
        </product>
    </function>-->

    <function name="aero/coefficient/dCz_sb">
        <description>
           Cz due speed brake coefficient.

           Source: TN-D-8176
        </description>
        <product>
            <v>0.9333</v><!-- ref area is different -->
            <property>fcs/speedbrake-pos-norm</property>
            <table name="table/dCz_sb">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-10 0.0087
-05 0.0044
 00 0.0000
 05 -.0044
 10 -.0087
 15 -.0130
 20 -.0171
 25 -.0212
 30 -.0250
 35 -.0287
 40 -.0322
 45 -.0354
 50 -.0383
 55 -.0410
 60 -.0433
 70 -.0470
 80 -.0493
 90 -.0500
                 </tableData>
            </table>
        </product>
    </function>

    <function name="aero/coefficient/Cz_q">
        <description>
           Cz due to pitch rate coefficient.
        </description>
        <product>
            <property>aero/ci2vel</property>
            <property>velocities/q-rad_sec</property>
            <table name="table/Cz_q">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 -23.9
-15 -23.9
-10 -23.9
-05 -29.5
 00 -29.5
 05 -30.5
 10 -31.3
 15 -30.1
 20 -27.7
 25 -28.2
 30 -29.0
 35 -29.8
 40 -38.3
 45 -35.3
 50 -32.3
 55 -27.3
 60 -25.2
 70 -27.3
 80 -9.35
 90 -2.16
                </tableData>
            </table>
        </product>
    </function>

    <function name="aero/coefficient/dCz_q-lef">
        <description>
           Cz due to pitch rate due to leading edge flaps coefficient.

           Source for alpha 50+: TN-D-8176
        </description>
        <product>
            <property>aero/ci2vel</property>
            <property>velocities/q-rad_sec</property>
            <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
            <table name="table/dCz_q-lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 15.1
-15 15.1
-10 15.1
-05 3.70
 00 .600
 05 -1.3
 10 0.30
 15 -3.8
 20 -4.6
 25 -.20
 30 -2.7 
 35 -3.5
 40 -1.3
 45 -.65
 50 0.00
 55 0.00
 60 0.00
 70 0.00
 80 0.00
 90 0.00
                 </tableData>
            </table>
        </product>
    </function>        

    <function name="aero/coefficient/Cz_t">
        <description>
           Total Z Coefficient
        </description>
        <product>
            <sum>
                <p>aero/coefficient/CLz</p>
                <p>aero/coefficient/CDz</p>
                <p>aero/coefficient/Cz</p>
                <p>aero/coefficient/dCz_lef</p>
                <p>aero/coefficient/dCz_sb</p>
                <p>aero/coefficient/Cz_q</p>
                <p>aero/coefficient/dCz_q-lef</p>
            </sum>
        </product>
    </function>


    <axis name="Z">

        <function name="aero/coefficient/Z_t-lbf">
            <description>Total Z force</description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>              
                <property>aero/coefficient/Cz_t</property>
            </product>
        </function>         

    </axis>











    <function name="aero/function/n_dh">
        <description>
           Elevator effectiveness factor.
        </description>
        <product>
            <table name="table/n_dh">
                <independentVar lookup="row">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                <tableData>
-25 1.0
-10 1.0
 00 1.0
 10 1.0
 25 .95
                 </tableData>
            </table>
        </product>
    </function>

    <axis name="PITCH">

        <function name="aero/coefficient/Cm">
            <description>
               Cm coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <p>aero/function/n_dh</p>
                <table name="table/Cm">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">aero/beta-deg</independentVar>
                    <independentVar lookup="table">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                    <tableData breakPoint="-25.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  0.8793  0.2242  0.2242  0.2205  0.2102  0.2111  0.2211  0.2167  0.2149  0.2156  0.2151  0.2192  0.2250  0.2274  0.2346  0.2450  0.2490  0.2490  0.2563
-15  0.1983  0.1973  0.2100  0.2113  0.1976  0.2116  0.2167  0.2156  0.2165  0.2169  0.2164  0.2169  0.2081  0.2016  0.1902  0.2035  0.2033  0.1898  0.1923
-10  0.1697  0.1932  0.2210  0.2074  0.2019  0.2110  0.2146  0.2211  0.2222  0.2244  0.2156  0.2086  0.2048  0.1986  0.1972  0.2000  0.2143  0.1878  0.1645
 -5  0.2085  0.2273  0.2010  0.1950  0.1913  0.1900  0.1862  0.1787  0.1746  0.1706  0.1672  0.1711  0.1741  0.1779  0.1821  0.1859  0.1905  0.2162  0.1988
  0  0.2050  0.2040  0.1998  0.1973  0.1971  0.1963  0.1947  0.1918  0.1916  0.1911  0.1913  0.1913  0.1906  0.1916  0.1923  0.1962  0.1963  0.2025  0.2021
  5  0.1953  0.2073  0.2088  0.2093  0.2111  0.2121  0.2109  0.2097  0.2100  0.2100  0.2114  0.2110  0.2102  0.2098  0.2101  0.2096  0.2087  0.2080  0.2003
 10  0.2043  0.2180  0.2203  0.2258  0.2306  0.2319  0.2327  0.2337  0.2402  0.2416  0.2412  0.2395  0.2384  0.2369  0.2355  0.2321  0.2265  0.2234  0.2098
 15  0.2255  0.2393  0.2558  0.2598  0.2634  0.2644  0.2674  0.2692  0.2691  0.2711  0.2690  0.2688  0.2677  0.2639  0.2621  0.2582  0.2529  0.2373  0.2238
 20  0.2030  0.2303  0.2530  0.2655  0.2711  0.2752  0.2777  0.2777  0.2767  0.2776  0.2749  0.2739  0.2743  0.2736  0.2715  0.2644  0.2524  0.2223  0.2014
 25  0.1660  0.2058  0.2380  0.2593  0.2691  0.2670  0.2668  0.2619  0.2601  0.2599  0.2587  0.2573  0.2579  0.2545  0.2581  0.2509  0.2299  0.1980  0.1571
 30  0.1463  0.1100  0.1455  0.2105  0.2326  0.2565  0.2614  0.2636  0.2645  0.2642  0.2654  0.2639  0.2601  0.2587  0.2546  0.2332  0.1695  0.1354  0.1679
 35  0.1080  0.0768  0.1080  0.1233  0.1652  0.1701  0.2051  0.2284  0.2378  0.2419  0.2420  0.2405  0.2420  0.2316  0.2025  0.1638  0.1446  0.1140  0.1485
 40  0.1300  0.0613  0.0880  0.1240  0.1579  0.1781  0.1861  0.1989  0.2059  0.2056  0.1843  0.1883  0.1869  0.1549  0.1564  0.1196  0.0864  0.0608  0.1275
 45  0.1165  0.0955  0.0963  0.0893  0.1149  0.1358  0.1474  0.1302  0.1384  0.1383  0.1419  0.1318  0.1055  0.0916  0.0836  0.0569  0.0653  0.0628  0.0824
 50 -0.0165 -0.0105 -0.0270  0.0275  0.1024  0.0983  0.0816  0.0731  0.0880  0.1138  0.1062  0.0844  0.0767  0.0719  0.0802  0.0163 -0.0430 -0.0302 -0.0354
 55  0.0365  0.0258 -0.0913  0.0083  0.1112  0.0748  0.0363  0.0828  0.0573  0.1076  0.0718  0.0272  0.0233  0.0453  0.0601 -0.0434 -0.1428 -0.0282 -0.0157
 60  0.0008  0.0083 -0.0505 -0.0320 -0.0406 -0.0524 -0.0416 -0.0394 -0.0370 -0.0322 -0.0414 -0.0483 -0.0655 -0.0697 -0.0873 -0.0793 -0.0961 -0.0380 -0.0432
 70 -0.2880 -0.2855 -0.2608 -0.2845 -0.2494 -0.2401 -0.1609 -0.1902 -0.1804 -0.2001 -0.2017 -0.1944 -0.1787 -0.1908 -0.1867 -0.2227 -0.1984 -0.2249 -0.2268
 80 -0.3355 -0.3680 -0.3718 -0.3573 -0.3051 -0.2984 -0.3080 -0.3102 -0.2916 -0.3067 -0.3182 -0.2829 -0.2892 -0.2906 -0.2901 -0.3448 -0.3593 -0.3535 -0.3218
 90 -0.4993 -0.5013 -0.4898 -0.4760 -0.4608 -0.4855 -0.4488 -0.4642 -0.4485 -0.4358 -0.4497 -0.4517 -0.4621 -0.4772 -0.4550 -0.4699 -0.4853 -0.4946 -0.4929
                    </tableData>
                    <tableData breakPoint="-10.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  0.1592  0.1410  0.1357  0.1236  0.0984  0.0939  0.0999  0.1018  0.1038  0.1048  0.0977  0.1008  0.1025  0.1051  0.1162  0.1413  0.1535  0.1589  0.1764
-15  0.1219  0.1106  0.1118  0.1066  0.0786  0.0779  0.0749  0.0681  0.0641  0.0599  0.0619  0.0683  0.0716  0.0722  0.0727  0.1001  0.1059  0.1045  0.1138
-10  0.0895  0.0887  0.1017  0.0796  0.0590  0.0558  0.0515  0.0486  0.0425  0.0308  0.0410  0.0452  0.0494  0.0514  0.0552  0.0756  0.0980  0.0849  0.0860
 -5  0.0773  0.0835  0.0648  0.0538  0.0400  0.0393  0.0351  0.0301  0.0319  0.0281  0.0281  0.0296  0.0321  0.0333  0.0343  0.0481  0.0588  0.0788  0.0715
  0  0.0788  0.0790  0.0685  0.0648  0.0690  0.0678  0.0685  0.0691  0.0689  0.0687  0.0675  0.0689  0.0615  0.0629  0.0628  0.0689  0.0709  0.0834  0.0754
  5  0.0765  0.0685  0.0763  0.0793  0.0804  0.0789  0.0802  0.0788  0.0775  0.0751  0.0775  0.0767  0.0769  0.0771  0.0772  0.0774  0.0754  0.0692  0.0813
 10  0.0518  0.0593  0.0640  0.0633  0.0711  0.0721  0.0742  0.0739  0.0749  0.0801  0.0762  0.0777  0.0770  0.0773  0.0762  0.0671  0.0664  0.0630  0.0540
 15  0.0705  0.0693  0.0833  0.0898  0.0922  0.0916  0.0960  0.0977  0.1005  0.0984  0.0990  0.0981  0.0983  0.0962  0.0909  0.0872  0.0815  0.0679  0.0678
 20  0.0480  0.0490  0.0655  0.0755  0.0832  0.0830  0.0850  0.0866  0.0909  0.0928  0.0945  0.0917  0.0882  0.0821  0.0789  0.0730  0.0626  0.0450  0.0440
 25  0.0285  0.0320  0.0480  0.0643  0.0725  0.0735  0.0733  0.0705  0.0725  0.0742  0.0700  0.0714  0.0682  0.0647  0.0678  0.0587  0.0428  0.0247  0.0221
 30  0.0300 -0.0175  0.0018  0.0268  0.0446  0.0652  0.0720  0.0738  0.0755  0.0775  0.0728  0.0730  0.0698  0.0653  0.0583  0.0412  0.0150 -0.0057  0.0441
 35  0.0255 -0.0158 -0.0195 -0.0080  0.0110  0.0210  0.0349  0.0443  0.0529  0.0499  0.0501  0.0469  0.0332  0.0349  0.0239 -0.0030 -0.0082 -0.0056  0.0357
 40  0.0738  0.0225 -0.0070 -0.0010  0.0066  0.0095  0.0110  0.0135  0.0130  0.0091 -0.0046 -0.0032 -0.0237 -0.0207 -0.0234 -0.0323 -0.0380 -0.0062  0.0407
 45  0.0315 -0.0133 -0.0188 -0.0445 -0.0393 -0.0272 -0.0399 -0.0434 -0.0272 -0.0283 -0.0344 -0.0455 -0.0608 -0.0635 -0.0702 -0.0754 -0.0476 -0.0433 -0.0001
 50 -0.0116  0.0033 -0.0045 -0.0044  0.0286  0.0072 -0.0270 -0.0426 -0.0246  0.0045 -0.0052 -0.0291 -0.0377 -0.0423 -0.0338 -0.0561 -0.0610 -0.0573 -0.0718
 55  0.0130  0.0099 -0.1008 -0.0399  0.0568  0.0298  0.0008 -0.0046  0.0066  0.0437  0.0049 -0.0428 -0.0490 -0.0283 -0.0149 -0.1111 -0.1730 -0.0647 -0.0583
 60 -0.0641 -0.0024 -0.0048 -0.1766 -0.0825 -0.0956 -0.0861 -0.0798 -0.0676 -0.0532 -0.0750 -0.0947 -0.1179 -0.1215 -0.1385 -0.2334 -0.0610 -0.0590 -0.1204
 70 -0.3329 -0.3479 -0.3333 -0.3488 -0.3433 -0.3295 -0.2687 -0.3015 -0.2919 -0.3117 -0.3078 -0.2952 -0.2804 -0.2999 -0.3033 -0.3089 -0.2931 -0.3079 -0.2930
 80 -0.4160 -0.4599 -0.4776 -0.4776 -0.4181 -0.4098 -0.4097 -0.4184 -0.3986 -0.4126 -0.4336 -0.4076 -0.4149 -0.4091 -0.4014 -0.4611 -0.4611 -0.4433 -0.3996
 90 -0.6178 -0.6141 -0.5995 -0.5909 -0.5398 -0.5760 -0.5508 -0.5754 -0.5662 -0.5602 -0.5619 -0.5517 -0.5582 -0.5777 -0.5599 -0.5684 -0.5770 -0.5916 -0.5952
                    </tableData>
                    <tableData breakPoint="0.0">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.0978 0.0719 0.0621 0.0430 0.0054 0.0023 0.0006 0.0062 0.0114 0.0127 0.0001 0.0023 0.0006 0.0033 0.0177 0.0550 0.0740 0.0840 0.1100
-15 0.0560 0.0357 0.0264 0.0163 -.0240 -.0372 -.0472 -.0590 -.0674 -.0755 -.0712 -.0600 -.0460 -.0393 -.0287 0.0110 0.0220 0.0310 0.0460
-10 0.0342 0.0167 0.0194 -.0089 -.0410 -.0510 -.0608 -.0700 -.0813 -.1025 -.0793 -.0673 -.0576 -.0500 -.0424 -.0100 0.0180 0.0140 0.0320
-05 -.0240 -.0240 -.0390 -.0550 -.0750 -.0773 -.0802 -.0802 -.0774 -.0744 -.0774 -.0782 -.0784 -.0782 -.0770 -.0572 -.0400 -.0251 -.0260
 00 -.0550 -.0460 -.0590 -.0640 -.0660 -.0660 -.0639 -.0615 -.0605 -.0598 -.0600 -.0606 -.0608 -.0617 -.0621 -.0606 -.0587 -.0484 -.0517
 05 -.0460 -.0640 -.0550 -.0520 -.0514 -.0507 -.0509 -.0501 -.0499 -.0498 -.0500 -.0518 -.0526 -.0532 -.0537 -.0545 -.0564 -.0619 -.0651
 10 -.0670 -.0620 -.0560 -.0530 -.0495 -.0484 -.0467 -.0457 -.0444 -.0437 -.0448 -.0458 -.0480 -.0490 -.0498 -.0534 -.0555 -.0619 -.0658
 15 -.0670 -.0770 -.0680 -.0590 -.0536 -.0514 -.0489 -.0456 -.0419 -.0407 -.0410 -.0422 -.0432 -.0447 -.0484 -.0536 -.0609 -.0715 -.0613
 20 -.0570 -.0710 -.0620 -.0520 -.0478 -.0518 -.0498 -.0463 -.0384 -.0342 -.0329 -.0366 -.0426 -.0532 -.0555 -.0620 -.0705 -.0800 -.0660
 25 -.0640 -.0880 -.0770 -.0670 -.0548 -.0539 -.0530 -.0520 -.0499 -.0507 -.0501 -.0506 -.0526 -.0439 -.0560 -.0649 -.0761 -.0888 -.0633
 30 -.0450 -.1050 -.0920 -.0920 -.0782 -.0608 -.0529 -.0500 -.0471 -.0459 -.0510 -.0520 -.0542 -.0612 -.0680 -.0847 -.0849 -.0971 -.0364
 35 -.0220 -.0720 -.0920 -.0880 -.0738 -.0639 -.0594 -.0572 -.0567 -.0605 -.0605 -.0625 -.0729 -.0747 -.0804 -.0930 -.0974 -.0775 -.0279
 40 0.0450 0.0050 -.0520 -.0610 -.0662 -.0729 -.0739 -.0789 -.0820 -.0835 -.0917 -.0971 -.1252 -.1071 -.1116 -.1057 -.0979 -.0402 0.0022
 45 -.0010 -.0520 -.0600 -.0920 -.0927 -.0861 -.1056 -.0966 -.0862 -.0923 -.0975 -.1080 -.1168 -.1209 -.1243 -.1234 -.0897 -.0820 -.0294
 50 -.0090 -.0130 -.0170 -.0350 -.0780 -.0713 -.0774 -.0890 -.0913 -.0826 -.0898 -.1112 -.1201 -.1277 -.1222 -.1220 -.0852 -.0648 -.0624
 55 -.0510 -.0180 -.0650 -.0530 -.0477 -.0520 -.0583 -.0663 -.0830 -.0738 -.0851 -.1053 -.1050 -.0988 -.1000 -.1076 -.1152 -.0589 -.1047
 60 -.1830 -.1480 -.1730 -.1720 -.1512 -.1428 -.1118 -.1094 -.1266 -.1414 -.1436 -.1437 -.1521 -.1459 -.1530 -.1709 -.1741 -.1475 -.1841
 70 -.3830 -.3980 -.3820 -.3870 -.3869 -.3637 -.2706 -.2967 -.2944 -.3216 -.3252 -.3199 -.3123 -.3385 -.3487 -.3486 -.3445 -.3593 -.3444
 80 -.4830 -.5180 -.5280 -.5060 -.4850 -.4785 -.4804 -.4869 -.4605 -.4678 -.4883 -.4620 -.4744 -.4792 -.4821 -.5022 -.5242 -.5145 -.4788
 90 -.6330 -.6300 -.6160 -.6160 -.6067 -.6366 -.6053 -.6281 -.6217 -.6184 -.6163 -.6022 -.6073 -.6281 -.6115 -.6209 -.6210 -.6351 -.6381
                    </tableData>
                    <tableData breakPoint="10.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20  0.0006 -0.0225 -0.0289 -0.0525 -0.0986 -0.1186 -0.1159 -0.1084 -0.1047 -0.1076 -0.1194 -0.1168 -0.1180 -0.1110 -0.0973 -0.0469 -0.0235 -0.0168  0.0060
-15 -0.0331 -0.0571 -0.0722 -0.0970 -0.1481 -0.1627 -0.1715 -0.1791 -0.1910 -0.1960 -0.1926 -0.1810 -0.1681 -0.1616 -0.1547 -0.1025 -0.0791 -0.0634 -0.0416
-10 -0.0772 -0.1032 -0.1214 -0.1510 -0.1799 -0.1884 -0.1958 -0.2043 -0.2147 -0.2435 -0.2101 -0.2004 -0.1916 -0.1868 -0.1800 -0.1506 -0.1209 -0.1630 -0.0765
 -5 -0.1340 -0.1490 -0.1803 -0.1963 -0.2100 -0.2157 -0.2187 -0.2200 -0.2169 -0.2174 -0.2182 -0.2217 -0.2217 -0.2192 -0.2095 -0.1957 -0.1800 -0.1500 -0.1335
  0 -0.1325 -0.1473 -0.1753 -0.1828 -0.1835 -0.1835 -0.1828 -0.1809 -0.1874 -0.1863 -0.1875 -0.1886 -0.1936 -0.1871 -0.1870 -0.1874 -0.1766 -0.1454 -0.1333
  5 -0.1198 -0.1503 -0.1663 -0.1808 -0.1809 -0.1811 -0.1810 -0.1812 -0.1850 -0.1883 -0.1888 -0.1896 -0.1831 -0.1830 -0.1816 -0.1814 -0.1672 -0.1508 -0.1312
 10 -0.1045 -0.1245 -0.1385 -0.1555 -0.1651 -0.1654 -0.1771 -0.1798 -0.1852 -0.1826 -0.1826 -0.1786 -0.1793 -0.1690 -0.1701 -0.1617 -0.1436 -0.1308 -0.1136
 15 -0.1045 -0.1283 -0.1493 -0.1740 -0.1766 -0.1747 -0.1815 -0.1824 -0.1795 -0.1713 -0.1748 -0.1832 -0.1830 -0.1851 -0.1779 -0.1754 -0.1523 -0.1296 -0.1047
 20 -0.0633 -0.0860 -0.1058 -0.1195 -0.1556 -0.1646 -0.1601 -0.1559 -0.1529 -0.1495 -0.1493 -0.1484 -0.1781 -0.1880 -0.1936 -0.1558 -0.1399 -0.1238 -0.1010
 25 -0.0778 -0.1068 -0.1220 -0.1183 -0.1576 -0.1665 -0.1780 -0.1795 -0.1800 -0.1786 -0.1812 -0.1749 -0.1744 -0.1890 -0.1910 -0.1500 -0.1535 -0.1391 -0.1079
 30 -0.0988 -0.1838 -0.1833 -0.1920 -0.1942 -0.1786 -0.1743 -0.1713 -0.1682 -0.1685 -0.1685 -0.1695 -0.1777 -0.1810 -0.1780 -0.1776 -0.1688 -0.1695 -0.0847
 35 -0.1258 -0.1834 -0.2098 -0.2399 -0.2254 -0.2040 -0.1744 -0.1662 -0.1642 -0.1613 -0.1661 -0.1735 -0.1774 -0.1847 -0.1930 -0.2063 -0.1770 -0.1510 -0.0949
 40 -0.0660 -0.1361 -0.1471 -0.1704 -0.1591 -0.1408 -0.1442 -0.1512 -0.1739 -0.1604 -0.1700 -0.1751 -0.1596 -0.1787 -0.1824 -0.1975 -0.1697 -0.1602 -0.0936
 45 -0.1808 -0.1034 -0.1499 -0.2011 -0.1666 -0.1365 -0.1052 -0.1727 -0.2043 -0.1533 -0.1800 -0.1799 -0.1752 -0.1967 -0.2029 -0.2449 -0.1831 -0.1445 -0.2345
 50 -0.1890 -0.1630 -0.1558 -0.1750 -0.1151 -0.1109 -0.1195 -0.1220 -0.1223 -0.1054 -0.1101 -0.1290 -0.1291 -0.1216 -0.1010 -0.1498 -0.1353 -0.1446 -0.1717
 55 -0.0823 -0.0743 -0.1738 -0.0580  0.0026 -0.0445 -0.0936 -0.0602 -0.1013 -0.0664 -0.0940 -0.1303 -0.1264 -0.0968 -0.0746 -0.1357 -0.2531 -0.1550 -0.1590
 60 -0.1680 -0.1130 -0.1255 -0.1320 -0.1607 -0.1686 -0.1539 -0.1532 -0.1574 -0.1592 -0.1707 -0.1790 -0.1952 -0.1959 -0.2099 -0.1833 -0.1762 -0.1658 -0.2185
 70 -0.4044 -0.4060 -0.3781 -0.4095 -0.3307 -0.3296 -0.2586 -0.2651 -0.2015 -0.1675 -0.2141 -0.2519 -0.2588 -0.2709 -0.2670 -0.3796 -0.3480 -0.3762 -0.3745
 80 -0.5145 -0.5378 -0.5346 -0.5301 -0.4884 -0.4864 -0.4927 -0.4995 -0.4695 -0.4732 -0.4941 -0.4681 -0.4784 -0.4786 -0.4769 -0.5188 -0.5233 -0.5264 -0.5033
 90 -0.6378 -0.6333 -0.6178 -0.6231 -0.5870 -0.6176 -0.5869 -0.6112 -0.6070 -0.6058 -0.6059 -0.5942 -0.5956 -0.6066 -0.5803 -0.6164 -0.6110 -0.6265 -0.6310
                    </tableData>
                    <tableData breakPoint="25.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.1267 -0.1459 -0.1480 -0.1775 -0.2346 -0.2692 -0.2662 -0.2584 -0.2566 -0.2648 -0.2755 -0.2726 -0.2733 -0.2605 -0.2477 -0.1800 -0.1510 -0.1485 -0.1300
-15 -0.1590 -0.1879 -0.2124 -0.2566 -0.3234 -0.3397 -0.3467 -0.3485 -0.3655 -0.3660 -0.3637 -0.3516 -0.3405 -0.3339 -0.3325 -0.2628 -0.2218 -0.1965 -0.1653
-10 -0.1994 -0.2348 -0.2759 -0.3078 -0.3323 -0.3393 -0.3441 -0.3515 -0.3578 -0.3983 -0.3537 -0.3466 -0.3387 -0.3368 -0.3312 -0.3050 -0.2733 -0.2323 -0.1955
 -5 -0.2153 -0.2440 -0.2865 -0.3013 -0.3100 -0.3179 -0.3217 -0.3221 -0.3229 -0.3240 -0.3258 -0.3282 -0.3285 -0.3250 -0.3098 -0.3016 -0.2863 -0.2440 -0.2150
  0 -0.2038 -0.2348 -0.2778 -0.2928 -0.2944 -0.2943 -0.2957 -0.2958 -0.3023 -0.3009 -0.3005 -0.3004 -0.3013 -0.2992 -0.2959 -0.2962 -0.2802 -0.2358 -0.2056
  5 -0.1935 -0.2240 -0.2600 -0.2908 -0.2908 -0.2905 -0.2924 -0.2970 -0.3050 -0.3078 -0.3111 -0.3097 -0.2971 -0.2902 -0.2900 -0.2906 -0.2608 -0.2269 -0.1852
 10 -0.1433 -0.1870 -0.2210 -0.2568 -0.2748 -0.2740 -0.2872 -0.3035 -0.3172 -0.3083 -0.3137 -0.3048 -0.3006 -0.2836 -0.2788 -0.2642 -0.2284 -0.1925 -0.1508
 15 -0.1283 -0.1658 -0.2093 -0.2540 -0.2599 -0.2589 -0.2718 -0.2740 -0.2718 -0.2595 -0.2628 -0.2766 -0.2773 -0.2776 -0.2617 -0.2585 -0.2145 -0.1699 -0.1341
 20 -0.0708 -0.0985 -0.1395 -0.1795 -0.2634 -0.2759 -0.2716 -0.2641 -0.2660 -0.2621 -0.2645 -0.2581 -0.3130 -0.3248 -0.3300 -0.2484 -0.2088 -0.1653 -0.1369
 25 -0.0778 -0.1143 -0.1458 -0.1495 -0.2216 -0.2519 -0.2698 -0.2750 -0.2797 -0.2780 -0.2777 -0.2710 -0.2672 -0.2868 -0.2941 -0.2123 -0.2120 -0.1772 -0.1404
 30 -0.1100 -0.2063 -0.2095 -0.2245 -0.2291 -0.2133 -0.2115 -0.2078 -0.2071 -0.2060 -0.2038 -0.2098 -0.2183 -0.2191 -0.2145 -0.2068 -0.1953 -0.1605 -0.0927
 35 -0.1245 -0.1820 -0.2083 -0.2380 -0.2236 -0.2023 -0.1730 -0.1648 -0.1628 -0.1600 -0.1649 -0.1721 -0.1762 -0.1833 -0.1917 -0.2049 -0.1760 -0.1501 -0.0940
 40 -0.0425 -0.1063 -0.1270 -0.1473 -0.1395 -0.1264 -0.1293 -0.1359 -0.1545 -0.1441 -0.1535 -0.1586 -0.1602 -0.1636 -0.1674 -0.1781 -0.1545 -0.1348 -0.0733
 45 -0.0710 -0.0720 -0.0950 -0.1345 -0.1215 -0.1057 -0.1055 -0.1262 -0.1322 -0.1161 -0.1296 -0.1360 -0.1396 -0.1504 -0.1549 -0.1714 -0.1261 -0.1049 -0.1093
 50 -0.1328 -0.1130 -0.1120 -0.1000 -0.0736 -0.0939 -0.1304 -0.1513 -0.1479 -0.1336 -0.1343 -0.1492 -0.1529 -0.1566 -0.1471 -0.1633 -0.1768 -0.1823 -0.2058
 55 -0.1435 -0.1393 -0.2425 -0.1155 -0.0616 -0.0909 -0.1223 -0.0823 -0.1279 -0.0977 -0.1270 -0.1653 -0.1641 -0.1383 -0.1198 -0.1706 -0.2977 -0.1980 -0.2003
 60 -0.1330 -0.0655 -0.0630 -0.0708 -0.1186 -0.1508 -0.1604 -0.1689 -0.1670 -0.1627 -0.1752 -0.1857 -0.2054 -0.2113 -0.2305 -0.1833 -0.1736 -0.1780 -0.2456
 70 -0.4318 -0.4480 -0.4358 -0.4445 -0.3270 -0.3130 -0.2290 -0.2442 -0.2110 -0.2075 -0.3568 -0.1614 -0.1569 -0.2118 -0.2505 -0.3672 -0.3593 -0.3723 -0.3557
 80 -0.4418 -0.4955 -0.5230 -0.5160 -0.4579 -0.4614 -0.4732 -0.4860 -0.4625 -0.4726 -0.4372 -0.3740 -0.3917 -0.4176 -0.4536 -0.5136 -0.5192 -0.4915 -0.4378
 90 -0.5418 -0.5825 -0.4873 -0.5873 -0.5576 -0.5946 -0.5704 -0.5956 -0.5868 -0.5812 -0.5758 -0.5586 -0.5607 -0.5786 -0.5591 -0.5899 -0.6145 -0.5851 -0.5447
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCm_lef">
            <description>
               Cm due to leading edge flaps coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <difference>
                    <table name="table/dCm_lef">
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/beta-deg</independentVar>
                        <tableData>
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.0922 0.0559 0.0525 -.0338 -.0518 -.0605 -.0574 -.0554 -.0550 -.0503 -.0521 -.0483 -.0459 -.0404 -.0373 -.0193 0.0670 0.0704 0.1067
-15 0.0372 0.0062 -.0067 -.0217 -.0702 -.0860 -.1001 -.1000 -.1002 -.1012 -.0974 -.0939 -.0839 -.0837 -.0759 -.0274 -.0124 0.0005 0.0315
-10 0.0251 0.0006 0.0014 -.0229 -.0536 -.0634 -.0654 -.0656 -.0652 -.0647 -.0653 -.0659 -.0654 -.0631 -.0570 -.0263 -.0020 -.0028 -.0217
-05 -.0006 -.0193 -.0234 -.0321 -.0376 -.0389 -.0385 -.0386 -.0388 -.0387 -.0389 -.0387 -.0388 -.0392 -.0386 -.0321 -.0234 -.0193 -.0006
 00 -.0273 -.0246 -.0230 -.0231 -.0259 -.0255 -.0286 -.0271 -.0271 -.0267 -.0266 -.0272 -.0280 -.0267 -.0270 -.0242 -.0241 -.0257 -.0284
 05 -.0319 -.0272 -.0204 -.0270 -.0152 -.0148 -.0145 -.0138 -.0127 -.0128 -.0133 -.0141 -.0149 -.0157 -.0164 -.0182 -.0216 -.0287 -.0331
 10 -.0446 -.0368 -.0266 -.0166 -.0127 -.0113 -.0092 -.0057 -.0033 -.0016 -.0017 -.0025 -.0038 -.0049 -.0085 -.0124 -.0224 -.0326 -.0404
 15 -.0682 -.0587 -.0425 -.0197 0.0000 0.0026 0.0078 0.0158 0.0243 0.0323 0.0328 0.0290 0.0189 0.0120 0.0061 -.0136 -.0364 -.0526 -.0621
 20 -.0947 -.0851 -.0642 -.0536 -.0308 -.0293 -.0275 -.0234 -.0188 -.0161 -.0141 -.0136 -.0154 -.0180 -.0273 -.0501 -.0607 -.0816 -.0912
 25 -.1090 -.1235 -.0938 -.0777 -.0674 -.0648 -.0607 -.0558 -.0526 -.0455 -.0471 -.0479 -.0530 -.0563 -.0610 -.0713 -.0874 -.1171 -.1026<!-- -.1607 changed to -.0607-->
 30 -.0135 -.0857 -.0907 -.1013 -.0875 -.0983 -.0951 -.0913 -.0902 -.0871 -.0865 -.0896 -.0962 -.0997 -.1060 -.1198 -.1092 -.1042 -.0320
 35 0.0202 -.0510 -.0891 -.1086 -.1018 -.1014 -.1105 -.1117 -.1127 -.1151 -.1167 -.1230 -.1301 -.1387 -.1402 -.1470 -.1275 -.0894 -.0142
 40 -.0116 -.0639 -.0971 -.1156 -.1170 -.1142 -.1182 -.1160 -.1178 -.1206 -.1280 -.1347 -.1436 -.1512 -.1516 -.1502 -.1317 -.0985 -.0462
 45 -.0023 -.0164 -.0417 -.0987 -.0985 -.0975 -.1278 -.1042 -.1156 -.0979 -.1122 -.1225 -.1444 -.1340 -.1461 -.1463 -.0893 -.0640 -.0499
                         </tableData>
                    </table>
                    <table name="table/Cm_dh0">
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/beta-deg</independentVar>
                        <tableData>
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.0978 0.0719 0.0621 0.0430 0.0054 0.0023 0.0006 0.0062 0.0114 0.0127 0.0001 0.0023 0.0006 0.0033 0.0177 0.0550 0.0740 0.0840 0.1100
-15 0.0560 0.0357 0.0264 0.0163 -.0240 -.0372 -.0472 -.0590 -.0674 -.0755 -.0712 -.0600 -.0460 -.0393 -.0287 0.0110 0.0220 0.0310 0.0460
-10 0.0342 0.0167 0.0194 -.0089 -.0410 -.0510 -.0608 -.0700 -.0813 -.1025 -.0793 -.0673 -.0576 -.0500 -.0424 -.0100 0.0180 0.0140 0.0320
-05 -.0240 -.0240 -.0390 -.0550 -.0750 -.0773 -.0802 -.0802 -.0774 -.0744 -.0774 -.0782 -.0784 -.0782 -.0770 -.0572 -.0400 -.0251 -.0260
 00 -.0550 -.0460 -.0590 -.0640 -.0660 -.0660 -.0639 -.0615 -.0605 -.0598 -.0600 -.0606 -.0608 -.0617 -.0621 -.0606 -.0587 -.0484 -.0517
 05 -.0460 -.0640 -.0550 -.0520 -.0514 -.0507 -.0509 -.0501 -.0499 -.0498 -.0500 -.0518 -.0526 -.0532 -.0537 -.0545 -.0564 -.0619 -.0651
 10 -.0670 -.0620 -.0560 -.0530 -.0495 -.0484 -.0467 -.0457 -.0444 -.0437 -.0448 -.0458 -.0480 -.0490 -.0498 -.0534 -.0555 -.0619 -.0658
 15 -.0670 -.0770 -.0680 -.0590 -.0536 -.0514 -.0489 -.0456 -.0419 -.0407 -.0410 -.0422 -.0432 -.0447 -.0484 -.0536 -.0609 -.0715 -.0613
 20 -.0570 -.0710 -.0620 -.0520 -.0478 -.0518 -.0498 -.0463 -.0384 -.0342 -.0329 -.0366 -.0426 -.0532 -.0555 -.0620 -.0705 -.0800 -.0660
 25 -.0640 -.0880 -.0770 -.0670 -.0548 -.0539 -.0530 -.0520 -.0499 -.0507 -.0501 -.0506 -.0526 -.0439 -.0560 -.0649 -.0761 -.0888 -.0633
 30 -.0450 -.1050 -.0920 -.0920 -.0782 -.0608 -.0529 -.0500 -.0471 -.0459 -.0510 -.0520 -.0542 -.0612 -.0680 -.0847 -.0849 -.0971 -.0364
 35 -.0220 -.0720 -.0920 -.0880 -.0738 -.0639 -.0594 -.0572 -.0567 -.0605 -.0605 -.0625 -.0729 -.0747 -.0804 -.0930 -.0974 -.0775 -.0279
 40 0.0450 0.0050 -.0520 -.0610 -.0662 -.0729 -.0739 -.0789 -.0820 -.0835 -.0917 -.0971 -.1252 -.1071 -.1116 -.1057 -.0979 -.0402 0.0022
 45 -.0010 -.0520 -.0600 -.0920 -.0927 -.0861 -.1056 -.0966 -.0862 -.0923 -.0975 -.1080 -.1168 -.1209 -.1243 -.1234 -.0897 -.0820 -.0294
 50 -.0090 -.0130 -.0170 -.0350 -.0780 -.0713 -.0774 -.0890 -.0913 -.0826 -.0898 -.1112 -.1201 -.1277 -.1222 -.1220 -.0852 -.0648 -.0624
 55 -.0510 -.0180 -.0650 -.0530 -.0477 -.0520 -.0583 -.0663 -.0830 -.0738 -.0851 -.1053 -.1050 -.0988 -.1000 -.1076 -.1152 -.0589 -.1047
 60 -.1830 -.1480 -.1730 -.1720 -.1512 -.1428 -.1118 -.1094 -.1266 -.1414 -.1436 -.1437 -.1521 -.1459 -.1530 -.1709 -.1741 -.1475 -.1841
 70 -.3830 -.3980 -.3820 -.3870 -.3869 -.3637 -.2706 -.2967 -.2944 -.3216 -.3252 -.3199 -.3123 -.3385 -.3487 -.3486 -.3445 -.3593 -.3444
 80 -.4830 -.5180 -.5280 -.5060 -.4850 -.4785 -.4804 -.4869 -.4605 -.4678 -.4883 -.4620 -.4744 -.4792 -.4821 -.5022 -.5242 -.5145 -.4788
 90 -.6330 -.6300 -.6160 -.6160 -.6067 -.6366 -.6053 -.6281 -.6217 -.6184 -.6163 -.6022 -.6073 -.6281 -.6115 -.6209 -.6210 -.6351 -.6381
                        </tableData>
                    </table>
                </difference>
            </product>
        </function>

        <!--<function name="aero/coefficient/Cm_cg">
            <description>
               Cm due to CoG shift, page 44 of TP 1538
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <difference>
                    <v>0.35</v>
                    <p>aero/CG-pos-c</p>
                </difference>
                <p>aero/coefficient/Cz_t</p>
            </product>
        </function>-->

        <function name="aero/coefficient/dCm_sb">
            <description>
               Cm due speed brake coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <property>fcs/speedbrake-pos-norm</property>
                <table name="table/dCm_sb">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.0034
-15 -.0034
-10 -.0034
-05 -.0034
 00 -.0034
 05 0.0289
 10 0.0215
 15 0.0122
 20 0.0241
 25 0.0263
 30 -.0163
 35 -.0428
 40 -.0704
 45 -.0844
 50 -.0789
 55 -.0603
 60 -.0450
 70 -.0578
 80 -.0107
 90 -.0107
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCm_tef">
            <description>
               Cm due TEF coefficient.

               Page 180 of TP-1538
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <property>fcs/fly-by-wire/tef/tef-pos-norm</property>
                <table name="table/dCm_tef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
 00 -0.01
 05  0.02
 10  0.015
 15  0.002
 20  0.009
 25  0.014
 30 -0.016
 35 -0.028
 40 -0.0362
 45 -0.0333
 50 -0.0362
 55 -0.014
 60 -0.0169
 70 -0.034
 90 0.0
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCm_alpha">
            <description>
               Cm due to alpha coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <table name="table/dCm_alpha">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .019
-15 .019
-10 .019
-05 .019
 00 .019
 05 .019
 10 .02
 15 .04
 20 .04
 25 .05
 30 .06
 35 .06
 40 .06
 45 .06
 50 .06
 55 .06
 60 .06
 70 .06
 80 .06
 90 .06
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/Cm_q">
            <description>
               Cm due to pitch rate coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <property>aero/ci2vel</property>
                <property>velocities/q-rad_sec</property>
                <table name="table/Cm_q">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -6.84
-15 -6.84
-10 -6.84
-05 -3.42
 00 -5.48
 05 -5.45
 10 -6.02
 15 -6.70
 20 -5.69
 25 -6.00
 30 -6.20
 35 -6.40
 40 -6.60
 45 -6.00
 50 -5.50
 55 -5.00
 60 -4.50
 70 -3.50
 80 -5.60
 90 -4.04
                    </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCm_q-lef">
            <description>
               Cm due to pitch rate due to leading edge flaps coefficient.

               Source for alpha 50+: TN-D-8176
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <property>aero/ci2vel</property>
                <property>velocities/q-rad_sec</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <table name="table/dCm_q-lef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.367
-15 -.367
-10 -.367
-05 2.88
 00 .25
 05 .27
 10 -.21
 15 .36
 20 -1.26
 25 -2.51
 30 -1.66
 35 -1.72
 40 -1.2
 45 -.60
 50 0.000
 55 0.000
 60 0.000
 70 0.000
 80 0.000
 90 0.000
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCm_ds">
            <description>
               Cm due to deep stall coefficient
            </description>
            <product>
                <property>fcs/fly-by-wire/pitch/block15-horz-tail-factor</property>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/cbarw-ft</property>
                <table name="table/dCm_ds">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                    <tableData>
        -25     -10       0      10      15      20      25
 30 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000 0.00000
 35 0.00000 0.00000 0.00000 0.00000 -.01130 -.01320 0.00000
 40 0.00000 0.01000 0.01000 0.02000 0.00410 0.02970 0.02540
 45 0.04800 0.05700 0.06400 0.07000 0.07060 0.05060 0.04070
 50 0.03900 0.05400 0.10500 0.07500 0.07920 0.07470 0.08220
 55 0.00000 0.02500 0.07500 0.04000 0.04160 0.05000 0.05830
 60 0.08400 0.08000 0.10600 0.10000 0.08860 0.07760 0.07850
 70 0.09900 0.07500 0.13200 0.02000 0.02875 0.03610 0.04680
 80 0.02000 0.01000 0.05000 0.00000 0.02180 -.02510 -.02100
 90 0.00000 0.01000 0.04000 0.00000 -.03445 -.03780 -.03780
                    </tableData>
                </table>
            </product>
        </function>

    </axis>










    <function name="aero/coefficient/Cy">
        <description>
           Cy coefficient
        </description>                
        <table name="table/Cy">
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.3677 0.3070 0.2460 0.1844 0.1062 0.0850 0.0677 0.0380 0.0186 0.0000 -.0232 -.0467 -.0747 -.1078 -.1421 -.2221 -.2861 -.3461 -.4081
-15 0.4019 0.3220 0.2651 0.1964 0.1332 0.1039 0.0753 0.0442 0.0175 0.0000 -.0188 -.0402 -.0681 -.1004 -.1317 -.1930 -.2540 -.3190 -.3980
-10 0.4367 0.3823 0.3185 0.2462 0.1513 0.1156 0.0760 0.0434 0.0161 0.0000 -.0124 -.0430 -.0792 -.1171 -.1542 -.2482 -.3212 -.3842 -.4382
-05 0.5538 0.4778 0.3758 0.2818 0.1833 0.1449 0.1055 0.0662 0.0325 0.0000 -.0420 -.0763 -.1177 -.1575 -.2072 -.3041 -.4001 -.5013 -.5794
 00 0.6218 0.5258 0.4208 0.3088 0.2014 0.1553 0.1138 0.0726 0.0371 0.0000 -.0394 -.0764 -.1191 -.1674 -.2134 -.3198 -.4315 -.5369 -.6400
 05 0.6544 0.5514 0.4294 0.3124 0.2028 0.1607 0.1133 0.0767 0.0331 0.0000 -.0383 -.0819 -.1233 -.1705 -.2173 -.3257 -.4430 -.5506 -.6514
 10 0.6255 0.5185 0.4225 0.3065 0.2016 0.1597 0.1131 0.0748 0.0345 0.0000 -.0383 -.0786 -.1204 -.1668 -.2171 -.3204 -.4347 -.5313 -.6371
 15 0.5885 0.4665 0.3755 0.2875 0.1837 0.1473 0.1069 0.0652 0.0298 0.0000 -.0383 -.0770 -.1200 -.1642 -.2056 -.3091 -.3966 -.4868 -.6100
 20 0.5783 0.4633 0.3383 0.2563 0.1814 0.1504 0.1116 0.0703 0.0332 0.0000 -.0248 -.0558 -.0984 -.1366 -.1729 -.2479 -.3280 -.4542 -.5698
 25 0.5005 0.4195 0.3005 0.2295 0.1643 0.1409 0.1029 0.0654 0.0343 0.0000 -.0335 -.0677 -.1028 -.1369 -.1692 -.2337 -.3044 -.4241 -.5030
 30 0.3751 0.3161 0.2291 0.1411 0.0927 0.1057 0.0911 0.0630 0.0297 0.0000 -.0306 -.0647 -.0906 -.1159 -.1353 -.1841 -.2743 -.3600 -.4189
 35 0.3292 0.2952 0.2112 0.1472 0.0857 0.0581 0.0651 0.0563 0.0264 0.0000 -.0214 -.0513 -.0806 -.0971 -.1022 -.1632 -.2282 -.3141 -.3488
 40 0.4470 0.3885 0.3025 0.2135 0.0748 0.0531 0.0303 0.0360 0.0123 0.0000 -.0320 -.0484 -.0664 -.0958 -.1075 -.1539 -.1575 -.1807 -.2242
 45 0.1634 0.0894 0.0444 0.0894 0.0782 0.0612 0.0458 0.0398 0.0279 0.0000 -.0868 -.1048 -.1365 -.1541 -.1830 -.1940 -.1506 -.1951 -.2662
 50 0.1366 0.1036 0.0916 0.1556 0.0866 0.0785 0.0555 0.0399 0.0302 0.0000 -.0178 -.0791 -.1060 -.1177 -.1508 -.2201 -.1565 -.1679 -.2008
 55 0.1735 0.1355 0.1795 0.1725 0.1104 0.0926 0.0663 0.0460 0.0424 0.0000 -.0087 -.0718 -.1065 -.1225 -.1468 -.2090 -.2153 -.1709 -.2107
 60 0.2233 0.1713 0.2083 0.1883 0.1230 0.1051 0.0788 0.0546 0.0474 0.0000 -.0048 -.0571 -.0840 -.1047 -.1242 -.1885 -.2077 -.1719 -.2099
 70 0.2609 0.2279 0.1739 0.1469 0.1074 0.0941 0.0765 0.0564 0.0371 0.0000 -.0113 -.0300 -.0477 -.0715 -.0859 -.1266 -.1534 -.2078 -.2421
 80 0.3055 0.2595 0.2165 0.1635 0.1096 0.0871 0.0753 0.0498 0.0212 0.0000 -.0203 -.0361 -.0655 -.0804 -.1027 -.1554 -.2075 -.2495 -.2954
 90 0.3078 0.2498 0.1998 0.1568 0.1089 0.0843 0.0658 0.0446 0.0203 0.0000 -.0263 -.0418 -.0611 -.0836 -.1068 -.1547 -.1986 -.2474 -.3047
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cy_dr">
        <description>
           Cy due to rudder coefficient
        </description>                
        <table name="table/Cy_dr">
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.4196 0.3510 0.2977 0.2414 0.1906 0.1827 0.1760 0.1446 0.1264 0.0945 0.0772 0.0538 0.0320 -.0018 -.0465 -.0970 -.1530 -.2050 -.2730
-15 0.4427 0.3724 0.3174 0.2511 0.2112 0.2011 0.1772 0.1445 0.1184 0.0940 0.0772 0.0562 0.0311 -.0067 -.0436 -.0830 -.1380 -.1930 -.2630
-10 0.4833 0.4258 0.3790 0.3075 0.2320 0.2096 0.1780 0.1412 0.1105 0.0931 0.0779 0.0540 0.0190 -.0229 -.0651 -.1420 -.2130 -.2600 -.3170
-05 0.6060 0.5400 0.4750 0.3640 0.2611 0.2271 0.1901 0.1528 0.1192 0.0827 0.0522 0.0158 -.0255 -.0703 -.1178 -.2213 -.3327 -.4000 -.4680
 00 0.6350 0.5660 0.4960 0.3800 0.2698 0.2407 0.1979 0.1572 0.1202 0.0821 0.0492 0.0147 -.0297 -.0788 -.1309 -.2407 -.3564 -.4250 -.4950
 05 0.6600 0.5990 0.5160 0.3960 0.2806 0.2500 0.2038 0.1616 0.1190 0.0849 0.0500 0.0101 -.0318 -.0815 -.1332 -.2481 -.3668 -.4390 -.5100
 10 0.6960 0.5960 0.5240 0.4080 0.2908 0.2407 0.1979 0.1574 0.1152 0.0796 0.0456 0.0106 -.0390 -.0855 -.1374 -.2443 -.3619 -.4340 -.5350
 15 0.6710 0.5570 0.4770 0.3630 0.2599 0.2368 0.1999 0.1597 0.1196 0.0849 0.0492 0.0136 -.0333 -.0770 -.1236 -.2280 -.3396 -.4200 -.5350
 20 0.6550 0.5430 0.4380 0.3490 0.2371 0.2163 0.1941 0.1455 0.1181 0.0783 0.0473 0.0199 -.0179 -.0538 -.0913 -.2012 -.2911 -.4010 -.5100
 25 0.5700 0.4800 0.3920 0.3070 0.2184 0.2124 0.1925 0.1638 0.1249 0.0879 0.0546 0.0232 -.0160 -.0520 -.0897 -.1783 -.2651 -.3620 -.4590
 30 0.4000 0.3400 0.2640 0.1920 0.1182 0.1428 0.1596 0.1458 0.1217 0.0930 0.0568 0.0278 -.0026 -.0388 -.0760 -.1488 -.2219 -.3000 -.3600
 35 0.3340 0.3150 0.2530 0.1910 0.1029 0.0868 0.0927 0.1048 0.0829 0.0593 0.0439 0.0179 -.0112 -.0407 -.0687 -.1570 -.2196 -.2910 -.3100
 40 0.1520 0.1620 0.1190 0.0910 0.0369 0.0042 0.0064 -.0024 -.0064 -.0096 -.0377 -.0541 -.0850 -.1087 -.1438 -.1967 -.2260 -.2711 -.2624
 45 0.1890 0.1190 0.0890 0.1030 0.0721 0.0605 0.0554 0.0611 0.0425 0.0143 -.0656 -.0957 -.1198 -.1519 -.1691 -.1979 -.1835 -.2141 -.2827
 50 0.1420 0.0970 0.0930 0.1100 0.0760 0.0743 0.0617 0.0325 0.0290 0.0065 -.0306 -.0627 -.1022 -.1332 -.1556 -.1912 -.1719 -.1739 -.2190
 55 0.1590 0.1190 0.1600 0.1450 0.0930 0.0694 0.0464 0.0102 0.0061 -.0183 -.0384 -.0944 -.1225 -.1557 -.1753 -.2277 -.2434 -.2003 -.2400
 60 0.1760 0.1410 0.1750 0.1460 0.0952 0.0644 0.0423 0.0019 -.0112 -.0357 -.0464 -.0974 -.1185 -.1145 -.1705 -.2213 -.2515 -.2160 -.2518
 70 0.2400 0.2000 0.1700 0.1440 0.0874 0.0679 0.0561 0.0254 -.0017 -.0228 -.0390 -.0545 -.0697 -.0898 -.1161 -.1731 -.1991 -.2307 -.2705
 80 0.2950 0.2480 0.2080 0.1550 0.1110 0.0902 0.0731 0.0578 0.0328 0.0210 -.0034 -.0241 -.0535 -.0712 -.0992 -.1449 -.1978 -.2422 -.2889
 90 0.3000 0.2410 0.1910 0.1580 0.1054 0.0784 0.0628 0.0482 0.0252 0.0064 -.0112 -.0323 -.0634 -.0829 -.1004 -.1527 -.1861 -.2362 -.2997
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cy_lef">
        <description>
           Cy due to rudder coefficient
        </description>                
        <table name="table/Cy_lef">
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.3692 0.2991 0.2417 0.1692 0.1078 0.0874 0.0837 0.0572 0.0260 0.0000 -.0258 -.0592 -.0863 -.1209 -.1504 -.2106 -.2836 -.3396 -.4106
-15 0.4368 0.3797 0.3249 0.2636 0.1826 0.1456 0.1068 0.0701 0.0336 0.0000 -.0337 -.0702 -.1100 -.1500 -.1902 -.2712 -.3332 -.3882 -.4452
-10 0.5000 0.4441 0.3671 0.2896 0.1871 0.1475 0.1096 0.0757 0.0377 0.0000 -.0339 -.0708 -.1108 -.1513 -.1949 -.2978 -.3758 -.4528 -.5078
-05 0.5683 0.4913 0.3913 0.2943 0.1926 0.1490 0.1125 0.0723 0.0369 0.0000 -.0363 -.0765 -.1169 -.1644 -.2132 -.3148 -.4118 -.5130 -.5889
 00 0.6293 0.5313 0.4173 0.3053 0.2024 0.1582 0.1116 0.0729 0.0374 0.0000 -.0374 -.0776 -.1223 -.1712 -.2158 -.3196 -.4308 -.5443 -.6426
 05 0.6397 0.5367 0.4267 0.3097 0.2042 0.1630 0.1174 0.0775 0.0394 0.0000 -.0352 -.0785 -.1189 -.1689 -.2150 -.3218 -.4364 -.5448 -.6496
 10 0.6132 0.5192 0.4302 0.3142 0.2080 0.1631 0.1187 0.0784 0.0370 0.0000 -.0378 -.0774 -.1228 -.1664 -.2153 -.3196 -.4353 -.5237 -.6177
 15 0.5416 0.4876 0.4126 0.3066 0.2020 0.1576 0.1168 0.0718 0.0377 0.0000 -.0368 -.0784 -.1194 -.1636 -.2096 -.3143 -.4223 -.4947 -.5499
 20 0.4750 0.3750 0.2950 0.2300 0.1576 0.1254 0.0919 0.0590 0.0282 0.0000 -.0313 -.0670 -.1023 -.1374 -.1710 -.2452 -.3089 -.3869 -.4880
 25 0.4878 0.3708 0.2508 0.1578 0.1176 0.1174 0.0893 0.0585 0.0286 0.0000 -.0301 -.0566 -.0925 -.1126 -.1321 -.1714 -.2647 -.3850 -.5025
 30 0.3436 0.3226 0.2286 0.1396 0.0825 0.0801 0.0757 0.0549 0.0287 0.0000 -.0289 -.0527 -.0724 -.0939 -.1136 -.1694 -.2589 -.3511 -.3742
 35 0.2437 0.2267 0.1757 0.1307 0.0776 0.0602 0.0535 0.0407 0.0181 0.0000 -.0214 -.0537 -.0808 -.1009 -.1226 -.1766 -.2208 -.2714 -.2901
 40 0.1976 0.1776 0.1566 0.1286 0.0906 0.0737 0.0593 0.0505 0.0188 0.0000 -.0286 -.0516 -.0737 -.0938 -.1132 -.1503 -.1791 -.1996 -.2195
 45 0.1741 0.1251 0.1201 0.1320 0.1110 0.0854 0.0550 0.0339 0.0183 0.0000 -.0544 -.0929 -.1312 -.1581 -.1766 -.1977 -.1859 -.1900 -.2385
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cy_da">
        <description>
           Cy due to aileron coefficient
        </description>                
        <table name="table/Cy_da">
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.3838 0.3204 0.2946 0.2275 0.1467 0.1200 0.1010 0.0717 0.0500 0.0281 0.0028 -.0154 -.0412 -.0694 -.0949 -.1760 -.2440 -.2700 -.3340
-15 0.4012 0.3333 0.2847 0.2150 0.1508 0.1247 0.0954 0.0678 0.0423 0.0197 0.0005 -.0202 -.0461 -.0809 -.1126 -.1770 -.2470 -.2950 -.3650
-10 0.4314 0.3741 0.3207 0.2418 0.1741 0.1349 0.1001 0.0680 0.0377 0.0222 0.0061 -.0245 -.0574 -.0935 -.1290 -.1956 -.2740 -.3300 -.3850
-05 0.6020 0.5160 0.4170 0.3160 0.2062 0.1668 0.1288 0.0892 0.0521 0.0164 -.0150 -.0528 -.0877 -.1308 -.1726 -.2831 -.3847 -.4831 -.5657
 00 0.6590 0.5630 0.4490 0.3300 0.2130 0.1799 0.1390 0.0963 0.0573 0.0197 -.0166 -.0528 -.0957 -.1350 -.1821 -.3000 -.4190 -.5326 -.6294
 05 0.6950 0.6020 0.4820 0.3510 0.2172 0.1820 0.1412 0.0990 0.0591 0.0214 -.0161 -.0497 -.0954 -.1380 -.1830 -.3051 -.4355 -.5553 -.6470
 10 0.6660 0.5800 0.4660 0.3480 0.2238 0.1879 0.1437 0.1038 0.0605 0.0229 -.0148 -.0527 -.0940 -.1373 -.1887 -.3044 -.4332 -.5456 -.6322
 15 0.6480 0.5370 0.4410 0.3300 0.2204 0.1801 0.1390 0.0993 0.0593 0.0237 -.0123 -.0489 -.0936 -.1332 -.1799 -.2899 -.4017 -.4962 -.6006
 20 0.5720 0.4820 0.3860 0.2980 0.1930 0.1520 0.1166 0.0750 0.0327 0.0028 -.0200 -.0510 -.0889 -.1273 -.1667 -.2716 -.3586 -.4536 -.5415
 25 0.4880 0.4070 0.3100 0.2380 0.1590 0.1381 0.1047 0.0727 0.0355 0.0026 -.0283 -.0604 -.0949 -.1305 -.1690 -.2478 -.3194 -.4177 -.4989
 30 0.3648 0.3061 0.2154 0.1340 0.0845 0.0978 0.0869 0.0608 0.0290 0.0002 -.0287 -.0586 -.0904 -.1165 -.1395 -.1890 -.2704 -.3614 -.4198
 35 0.2994 0.2420 0.1674 0.1058 0.0417 0.0217 0.0334 0.0285 0.0024 -.0225 -.0446 -.0699 -.0971 -.1160 -.1368 -.2009 -.2625 -.3371 -.3945
 40 0.0967 0.0825 0.0349 0.0078 -.0310 -.0492 -.0576 -.0533 -.0696 -.0840 -.1036 -.1271 -.1460 -.1763 -.1919 -.2328 -.2557 -.3029 -.3183
 45 0.0810 0.0531 0.0351 0.0212 0.0102 -.0205 -.0229 -.0361 -.0442 -.0494 -.0912 -.1570 -.1801 -.1989 -.2187 -.2301 -.2058 -.2404 -.3097
 50 0.0761 0.0531 0.0482 0.0482 0.0154 0.0135 -.0053 -.0296 -.0443 -.0598 -.0783 -.1238 -.1508 -.1465 -.2012 -.2347 -.2328 -.2361 -.2620
 55 0.0959 0.0721 0.1041 0.0881 0.0241 0.0054 -.0056 -.0441 -.0575 -.0849 -.0894 -.1331 -.1645 -.1724 -.2089 -.2714 -.2862 -.2529 -.2759
 60 0.1232 0.1021 0.1151 0.0882 0.0311 0.0001 -.0094 -.0503 -.0647 -.0920 -.0976 -.1289 -.1540 -.1714 -.1950 -.2546 -.2846 -.2656 -.2868
 70 0.2272 0.1961 0.1399 0.0880 0.0531 0.0247 0.0069 -.0224 -.0421 -.0497 -.0801 -.0890 -.0983 -.1196 -.1425 -.1745 -.2219 -.2780 -.3083
 80 0.2981 0.2535 0.2045 0.1432 0.0976 0.0788 0.0535 0.0446 0.0136 -.0046 -.0404 -.0582 -.0748 -.0950 -.1186 -.1638 -.2218 -.2731 -.3171
 90 0.2845 0.2302 0.1800 0.1510 0.0998 0.0777 0.0577 0.0351 0.0111 -.0048 -.0320 -.0476 -.0770 -.0989 -.1204 -.1735 -.2153 -.2572 -.3173
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cy_da-lef">
        <description>
           Cy due to aileron and leading edge flaps coefficient
        </description>                
        <table name="table/Cy_da-lef">
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">aero/beta-deg</independentVar>
            <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 0.3860 0.3207 0.2777 0.1838 0.1290 0.1215 0.1051 0.0758 0.0498 0.0247 -.0067 -.0334 -.0645 -.0939 -.1248 -.1790 -.2730 -.3160 -.3810
-15 0.4337 0.3695 0.3280 0.2622 0.2002 0.1669 0.1309 0.0961 0.0619 0.0268 -.0070 -.0415 -.0775 -.1183 -.1560 -.2170 -.2840 -.3250 -.3890
-10 0.4861 0.4153 0.3594 0.2824 0.2069 0.1715 0.1318 0.0978 0.0646 0.0305 -.0061 -.0415 -.0769 -.1130 -.1533 -.2310 -.3050 -.3630 -.4320
-05 0.6320 0.5470 0.4410 0.3320 0.2109 0.1775 0.1379 0.0940 0.0585 0.0202 -.0132 -.0538 -.0901 -.1326 -.1786 -.2971 -.4064 -.5121 -.5958
 00 0.6660 0.5750 0.4540 0.3370 0.2128 0.1776 0.1396 0.0957 0.0565 0.0209 -.0179 -.0552 -.0964 -.1347 -.1802 -.3049 -.4233 -.5437 -.6344
 05 0.6660 0.5790 0.4590 0.3350 0.2162 0.1801 0.1401 0.0992 0.0539 0.0190 -.0204 -.0569 -.0980 -.1424 -.1904 -.3091 -.4328 -.5514 -.6382
 10 0.6450 0.5620 0.4580 0.3360 0.2190 0.1828 0.1381 0.0955 0.0562 0.0164 -.0231 -.0582 -.1041 -.1462 -.1962 -.3136 -.4322 -.5393 -.6208
 15 0.5900 0.5370 0.4570 0.3300 0.2147 0.1780 0.1337 0.0950 0.0505 0.0151 -.0223 -.0583 -.0998 -.1438 -.1882 -.3026 -.4297 -.5085 -.5603
 20 0.4880 0.4110 0.3400 0.2720 0.1807 0.1512 0.1150 0.0776 0.0466 0.0162 -.0156 -.0489 -.0836 -.1150 -.1545 -.2450 -.3136 -.3841 -.4615
 25 0.4920 0.3630 0.2720 0.1810 0.1246 0.1206 0.0935 0.0676 0.0338 0.0010 -.0261 -.0531 -.0801 -.1061 -.1274 -.1823 -.2714 -.3631 -.4930
 30 0.3320 0.3150 0.2240 0.1320 0.0719 0.0731 0.0650 0.0458 0.0239 -.0032 -.0273 -.0595 -.0801 -.1000 -.1137 -.1726 -.2629 -.3540 -.3701
 35 0.2660 0.2230 0.1320 0.0840 0.0274 0.0248 0.0229 0.0129 -.0080 -.0215 -.0520 -.0758 -.1105 -.1253 -.1542 -.2105 -.2563 -.2938 -.3373
 40 0.1320 0.0870 0.0740 0.0500 0.0012 -.0165 -.0197 -.0465 -.0602 -.0807 -.1014 -.1290 -.1431 -.1644 -.1864 -.2334 -.2568 -.2685 -.3138
 45 0.1020 0.0520 0.0690 0.0650 0.0456 0.0212 0.0018 -.0260 -.0392 -.0611 -.1056 -.1607 -.1729 -.1961 -.2268 -.2456 -.2495 -.2313 -.2828
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cy_r">
        <description>
           Cy due to yaw rate coefficient.
        </description>
        <product>
            <property>aero/bi2vel</property>
            <property>velocities/r-rad_sec</property>
            <table name="table/Cy_r">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 1.44
-15 1.44
-10 1.44
-05 1.05
 00 .981
 05 .939
 10 .999
 15 .981
 20 .819
 25 .483
 30 .590
 35 1.21
 40 -.493
 45 -1.04
 50 -1.21
 55 -1.58
 60 -1.37
 70 -.0259
 80 -.127
 90 .193
                 </tableData>
            </table>
        </product>
    </function>

    <function name="aero/coefficient/dCy_r-lef">
        <description>
           Cy due to yaw rate due to leading edge flaps coefficient.

           Source for alpha 50+: TN-D-8176
        </description>
        <product>
            <property>aero/bi2vel</property>
            <property>velocities/r-rad_sec</property>
            <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
            <table name="table/Cy_r-lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 -.558
-15 -.558
-10 -.558
-05 -.198
 00 -.107
 05 .027
 10 -.085
 15 -.046
 20 .331
 25 .215
 30 .430
 35 -.060
 40 -.374
 45 -.187
 50 0.000
 55 0.000
 60 0.000
 70 0.000
 80 0.000
 90 0.000
                 </tableData>
            </table>
        </product>
    </function>        

    <function name="aero/coefficient/Cy_p">
        <description>
           Cy due to roll rate coefficient.
        </description>
        <product>
            <property>aero/bi2vel</property>
            <property>velocities/p-rad_sec</property>
            <table name="table/Cy_p">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 .0333
-15 .0333
-10 .0333
-05 -.177
 00 .0055
 05 .0679
 10 .310
 15 .234
 20 .344
 25 .362
 30 .611
 35 .529
 40 .298
 45 -2.27
 50 .971
 55 1.020
 60 2.90
 70 .451
 80 -.294
 90 -.261
                </tableData>
            </table>
        </product>
    </function>

    <function name="aero/coefficient/dCy_p-lef">
        <description>
           Cy due to roll rate due to leading edge flaps coefficient.

           Source for alpha 50+: TN-D-8176
        </description>
        <product>
            <property>aero/bi2vel</property>
            <property>velocities/p-rad_sec</property>
            <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
            <table name="table/Cy_p-lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <tableData>
-20 -.141
-15 -.141
-10 -.141
-05 .069
 00 -.197
 05 .0601
 10 -.121
 15 -.052
 20 .075
 25 .106
 30 -.077
 35 -.642
 40 -.255
 45 -.128
 50 0.000
 55 0.000
 60 0.000
 70 0.000
 80 0.000
 90 0.000
                 </tableData>
            </table>
        </product>
    </function>

    <function name="aero/coefficient/dCy_lef">
        <description>
           Cy due to leading edge flaps coefficient.
        </description>
        <product>
            <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
            <difference>
                <p>aero/coefficient/Cy_lef</p>
                <p>aero/coefficient/Cy</p>
            </difference>
        </product>
    </function>

    <function name="aero/coefficient/dCy_da-lef">
        <description>
           Cy due to aileron due to leading edge flaps coefficient
        </description>
        <product>
            <p>fcs/fly-by-wire/roll/aileron-pos-norm</p><!-- 1 = 20 degs (should it rely on absolute norm instead? [maybe]) -->
            <sum>
                <difference>
                    <p>aero/coefficient/Cy_da</p>
                    <p>aero/coefficient/Cy</p>
                </difference>
                <product>
                    <p>fcs/fly-by-wire/lef/lef-pos-r-norm</p>
                    <difference>
                        <p>aero/coefficient/Cy_da-lef</p>
                        <p>aero/coefficient/Cy_lef</p>                            
                        <difference>
                            <p>aero/coefficient/Cy_da</p>
                            <p>aero/coefficient/Cy</p>
                        </difference>
                    </difference>
                </product>
            </sum>
        </product>
    </function>

    <function name="aero/coefficient/dCy_dr">
        <description>
           Cy due to rudder coefficient
        </description>
        <product>
            <p>fcs/fly-by-wire/yaw/rudder-pos-norm</p><!-- 1 = 30 degs (should it rely on absolute norm instead? [probably]) -->
            <difference>
                <p>aero/coefficient/Cy_dr</p>
                <p>aero/coefficient/Cy</p>
            </difference>
        </product>
    </function>        

    <function name="aero/coefficient/Cy_t">
        <description>
           Total Side Force Coefficient
        </description>
        <product>
            <sum>
                <p>aero/coefficient/Cy</p>
                <p>aero/coefficient/dCy_lef</p>
                <p>aero/coefficient/dCy_da-lef</p>
                <p>aero/coefficient/dCy_dr</p>
                <p>aero/coefficient/Cy_r</p>
                <p>aero/coefficient/dCy_r-lef</p>
                <p>aero/coefficient/Cy_p</p>
                <p>aero/coefficient/dCy_p-lef</p>
            </sum>
        </product>
    </function>

    <axis name="Y">

        <function name="aero/coefficient/Y_t-lbf">
            <description>
               Side Force
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <p>aero/coefficient/Cy_t</p>
            </product>
        </function>

    </axis>






    <function name="aero/coefficient/Cn_dh0">
        <description>
            coefficient
        </description> 
            <table name="table/Cn_dh0">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>                       
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0551 -.0588 -.0496 -.0406 -.0219 -.0145 -.0075 -.0012 0.0002 0.0000 -.0090 0.0012 0.0059 0.0099 0.0141 0.0333 0.0425 0.0516 0.0477
-15 -.0561 -.0527 -.0456 -.0333 -.0248 -.0179 -.0127 -.0057 -.0018 0.0000 0.0025 0.0058 0.0111 0.0180 0.0238 0.0330 0.0450 0.0521 0.0553
-10 -.0666 -.0637 -.0545 -.0468 -.0297 -.0233 -.0145 -.0079 -.0031 0.0000 0.0028 0.0075 0.0150 0.0221 0.0302 0.0474 0.0552 0.0646 0.0674
-05 -.0902 -.0812 -.0664 -.0523 -.0366 -.0277 -.0194 -.0117 -.0055 0.0000 0.0063 0.0127 0.0214 0.0297 0.0398 0.0553 0.0693 0.0843 0.0933
 00 -.1058 -.0916 -.0749 -.0578 -.0413 -.0317 -.0226 -.0138 -.0066 0.0000 0.0061 0.0135 0.0225 0.0324 0.0414 0.0579 0.0746 0.0914 0.1055
 05 -.1074 -.0916 -.0754 -.0587 -.0415 -.0329 -.0227 -.0145 -.0064 0.0000 0.0061 0.0148 0.0231 0.0335 0.0421 0.0594 0.0762 0.0914 0.1079
 10 -.0981 -.0798 -.0718 -.0568 -.0416 -.0326 -.0232 -.0146 -.0062 0.0000 0.0063 0.0147 0.0240 0.0332 0.0427 0.0579 0.0727 0.0809 0.0995
 15 -.0812 -.0592 -.0537 -.0513 -.0375 -.0301 -.0212 -.0121 -.0052 0.0000 0.0063 0.0141 0.0243 0.0334 0.0404 0.0541 0.0566 0.0622 0.0840
 20 -.0684 -.0491 -.0290 -.0321 -.0308 -.0262 -.0179 -.0102 -.0042 0.0000 0.0018 0.0068 0.0152 0.0233 0.0296 0.0309 0.0279 0.0479 0.0674
 25 -.0528 -.0411 -.0223 -.0229 -.0240 -.0188 -.0129 -.0072 -.0029 0.0000 0.0033 0.0088 0.0147 0.0216 0.0258 0.0251 0.0242 0.0429 0.0547
 30 -.0300 0.0002 0.0115 0.0164 0.0091 -.0037 -.0024 0.0090 0.0025 0.0000 -.0029 -.0023 -.0013 -.0030 -.0019 -.0097 -.0042 0.0069 0.0370
 35 -.0098 0.0168 0.0392 0.0514 0.0396 0.0340 0.0163 0.0103 0.0069 0.0000 -.0097 -.0147 -.0157 -.0189 -.0295 -.0415 -.0291 -.0068 0.0194
 40 -.0025 0.0054 0.0683 0.0744 0.0506 0.0351 0.0207 0.0131 0.0052 0.0000 -.0071 -.0136 -.0216 -.0329 -.0440 -.0677 -.0622 0.0012 0.0202
 45 -.0111 0.0010 0.0294 0.0612 0.0451 0.0369 0.0293 0.0201 0.0116 0.0000 -.0237 -.0375 -.0460 -.0565 -.0694 -.0847 -.0530 -.0246 -.0126
 50 -.0256 -.0136 0.0058 0.0287 0.0254 0.0231 0.0233 0.0105 0.0078 0.0000 -.0063 -.0217 -.0355 -.0456 -.0548 -.0574 -.0346 -.0161 -.0046
 55 -.0302 -.0228 0.0130 0.0140 0.0040 0.0027 -.0023 -.0070 0.0043 0.0000 0.0028 -.0058 -.0172 -.0239 -.0258 -.0361 -.0355 0.0014 0.0073
 60 -.0188 -.0075 0.0211 0.0080 -.0061 -.0100 -.0174 -.0219 -.0079 0.0000 0.0075 0.0103 0.0043 -.0013 -.0019 -.0156 -.0284 0.0004 0.0110
 70 0.0296 0.0316 0.0210 0.0092 0.0003 -.0062 -.0128 -.0193 -.0187 0.0000 0.0039 0.0151 0.0163 0.0116 0.0059 -.0023 -.0141 -.0246 -.0228
 80 0.0264 0.0351 0.0254 0.0180 0.0133 0.0126 0.0107 0.0079 0.0055 0.0000 -.0001 0.0060 -.0033 -.0069 -.0075 -.0130 -.0198 -.0242 -.0209
 90 0.0274 0.0128 0.0118 0.0059 0.0051 0.0044 0.0031 0.0027 0.0017 0.0000 -.0018 -.0023 -.0031 -.0048 -.0048 -.0054 -.0111 -.0121 -.0163
             </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cn_lef">
        <description>
            coefficient
        </description>                
            <table name="table/Cn_lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0541 -.0563 -.0461 -.0495 -.0296 -.0208 -.0173 -.0100 -.0043 0.0000 0.0037 0.0076 0.0121 0.0186 0.0231 0.0428 0.0393 0.0494 0.0468
-15 -.0678 -.0728 -.0658 -.0539 -.0358 -.0282 -.0204 -.0126 -.0058 0.0000 0.0057 0.0125 0.0206 0.0288 0.0364 0.0539 0.0658 0.0730 0.0683
-10 -.0780 -.0773 -.0629 -.0555 -.0370 -.0289 -.0218 -.0142 -.0068 0.0000 0.0069 0.0141 0.0224 0.0301 0.0387 0.0572 0.0645 0.0715 0.0794
-05 -.0881 -.0851 -.0753 -.0556 -.0402 -.0308 -.0254 -.0141 -.0067 0.0000 0.0067 0.0144 0.0234 0.0328 0.0430 0.0586 0.0785 0.0872 0.0913
 00 -.1060 -.0929 -.0754 -.0593 -.0420 -.0319 -.0222 -.0135 -.0062 0.0000 0.0066 0.0143 0.0234 0.0340 0.0429 0.0595 0.0759 0.0938 0.1066
 05 -.1051 -.0877 -.0728 -.0573 -.0410 -.0324 -.0225 -.0140 -.0061 0.0000 0.0062 0.0149 0.0229 0.0336 0.0423 0.0589 0.0747 0.0877 0.1069
 10 -.0926 -.0797 -.0731 -.0580 -.0424 -.0327 -.0235 -.0154 -.0064 0.0000 0.0064 0.0115 0.0243 0.0330 0.0425 0.0579 0.0730 0.0796 0.0925
 15 -.0632 -.0670 -.0653 -.0549 -.0414 -.0316 -.0223 -.0135 -.0059 0.0000 0.0055 0.0143 0.0232 0.0325 0.0417 0.0533 0.0656 0.0673 0.0635
 20 -.0359 -.0191 -.0173 -.0230 -.0216 -.0174 -.0076 -.0058 -.0015 0.0000 0.0030 0.0087 0.0159 0.0227 0.0279 0.0292 0.0237 0.0253 0.0421
 25 -.0342 -.0208 -.0017 0.0063 -.0059 -.0094 -.0061 -.0029 -.0012 0.0000 0.0008 0.0038 0.0069 0.0078 0.0034 -.0088 -.0008 0.0183 0.0317
 30 -.0265 -.0047 0.0128 0.0249 0.0198 0.0114 0.0055 0.0057 0.0030 0.0000 -.0032 -.0077 -.0117 -.0201 -.0276 -.0332 -.0209 -.0034 0.0188
 35 0.0138 0.0391 0.0533 0.0553 0.0434 0.0397 0.0263 0.0206 0.0119 0.0000 -.0090 -.0134 -.0190 -.0263 -.0328 -.0444 -.0427 -.0279 -.0021
 40 0.0302 0.0357 0.0675 0.0645 0.0445 0.0330 0.0214 0.0156 0.0065 0.0000 -.0060 -.0136 -.0155 -.0266 -.0330 -.0532 -.0561 -.0240 0.0014
 45 0.0003 -.0038 0.0214 0.0400 0.0326 0.0261 0.0199 0.0130 0.0047 0.0000 -.0170 -.0369 -.0464 -.0533 -.0611 -.0681 -.0495 -.0245 -.0280
             </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cn_da">
        <description>
            coefficient
        </description>                
            <table name="table/Cn_da">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
   -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0639 -.0628 -.0616 -.0550 -.0359 -.0267 -.0188 -.0119 -.0093 -.0089 -.0081 -.0071 -.0043 -.0040 0.0020 0.0211 0.0277 0.0289 0.0300
-15 -.0619 -.0554 -.0490 -.0384 -.0336 -.0279 -.0232 -.0174 -.0137 -.0098 -.0066 -.0042 0.0002 0.0088 0.0134 0.0182 0.0288 0.0352 0.0417
-10 -.0679 -.0599 -.0544 -.0465 -.0396 -.0322 -.0254 -.0193 -.0139 -.0091 -.0055 -.0007 0.0047 0.0120 0.0186 0.0255 0.0334 0.0389 0.0469
-05 -.1080 -.0994 -.0838 -.0677 -.0460 -.0398 -.0321 -.0248 -.0176 -.0111 -.0054 0.0008 0.0074 0.0159 0.0246 0.0463 0.0624 0.0780 0.0866
 00 -.1234 -.1094 -.0915 -.0721 -.0498 -.0448 -.0377 -.0277 -.0193 -.0120 -.0056 0.0015 0.0092 0.0175 0.0268 0.0491 0.0685 0.0864 0.1004
 05 -.1245 -.1100 -.0939 -.0730 -.0496 -.0440 -.0360 -.0265 -.0176 -.0105 -.0037 0.0024 0.0109 0.0194 0.0285 0.0519 0.0728 0.0889 0.1034
 10 -.1118 -.1020 -.0894 -.0690 -.0486 -.0440 -.0349 -.0267 -.0171 -.0090 -.0020 0.0047 0.0132 0.0220 0.0318 0.0522 0.0726 0.0852 0.0950
 15 -.0967 -.0807 -.0737 -.0628 -.0472 -.0416 -.0379 -.0234 -.0136 -.0066 -.0003 0.0069 0.0158 0.0231 0.0328 0.0484 0.0593 0.0663 0.0823
 20 -.0670 -.0561 -.0505 -.0472 -.0358 -.0269 -.0198 -.0111 -.0029 -.0001 0.0015 0.0052 0.0121 0.0204 0.0273 0.0387 0.0420 0.0476 0.0585
 25 -.0353 -.0316 -.0201 -.0243 -.0175 -.0130 -.0079 -.0037 0.0012 0.0045 0.0072 0.0106 0.0159 0.0217 0.0277 0.0345 0.0303 0.0418 0.0455
 30 -.0187 0.0091 0.0230 0.0196 0.0132 0.0026 0.0021 0.0056 0.0082 0.0065 0.0039 0.0022 0.0030 0.0055 0.0045 -.0019 -.0053 0.0086 0.0364
 35 0.0070 0.0357 0.0548 0.0658 0.0468 0.0383 0.0219 0.0178 0.0138 0.0099 0.0011 -.0052 -.0082 -.0098 -.0174 -.0364 -.0254 -.0063 0.0224
 40 0.0056 0.0322 0.0831 0.0881 0.0563 0.0395 0.0271 0.0187 0.0127 0.0044 -.0009 -.0060 -.0131 -.0224 -.0328 -.0646 -.0578 -.0087 0.0179
 45 0.0046 0.0141 0.0404 0.0642 0.0513 0.0416 0.0319 0.0252 0.0164 0.0097 -.0062 -.0283 -.0386 -.0475 -.0583 -.0712 -.0474 -.0211 -.0116
 50 -.1090 -.0043 0.0157 0.0385 0.0386 0.0357 0.0282 0.0229 0.0196 0.0130 0.0071 -.0140 -.0211 -.0198 -.0452 -.0451 -.0223 -.0023 0.0043
 55 -.0100 -.0124 0.0256 0.0303 0.0237 0.0233 0.0166 0.0132 0.0193 0.0167 0.0175 -.0025 -.0042 -.0060 -.0183 -.0249 -.0202 0.0178 0.0154
 60 0.0047 -.0008 0.0281 0.0257 0.0165 0.0169 0.0115 0.0092 0.0207 0.0182 0.0236 0.0195 0.0158 0.0112 0.0039 -.0053 -.0077 0.0212 0.0157
 70 0.0470 0.0426 0.0308 0.0301 0.0253 0.0186 0.0160 0.0206 0.0190 0.0154 0.0245 0.0216 0.0283 0.0218 0.0156 0.0108 0.0101 -.0017 -.0061
 80 0.0410 0.0414 0.0368 0.0314 0.0251 0.0248 0.0233 0.0184 0.0156 0.0138 0.0154 0.0133 0.0101 0.0075 0.0081 0.0018 -.0036 -.0082 -.0078
 90 0.0320 0.0287 0.0237 0.0165 0.0165 0.0153 0.0151 0.0155 0.0138 0.0125 0.0113 0.0110 0.0101 0.0101 0.0117 0.0117 0.0045 -.0050 -.0038
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cn_da-lef">
        <description>
            coefficient
        </description>                
            <table name="table/Cn_da-lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0683 -.0615 -.0556 -.0519 -.0393 -.0314 -.0264 -.0199 -.0140 -.0095 -.0054 -.0029 0.0019 0.0074 0.0124 0.0251 0.0293 0.0354 0.0421
-15 -.0733 -.0702 -.0663 -.0551 -.0437 -.0372 -.0301 -.0233 -.0170 -.0108 -.0046 0.0017 0.0082 0.0159 0.0230 0.0343 0.0455 0.0497 0.0528
-10 -.0775 -.0683 -.0610 -.0527 -.0434 -.0385 -.0301 -.0240 -.0175 -.0108 -.0040 0.0027 0.0089 0.0161 0.0236 0.0327 0.0407 0.0479 0.0575
-05 -.1149 -.1067 -.0898 -.0716 -.0482 -.0429 -.0359 -.0267 -.0188 -.0113 -.0050 0.0024 0.0093 0.0186 0.0278 0.0511 0.0689 0.0856 0.0932
 00 -.1225 -.1106 -.0909 -.0722 -.0482 -.0428 -.0359 -.0256 -.0170 -.0099 -.0027 0.0042 0.0121 0.0197 0.0292 0.0533 0.0720 0.0915 0.1034
 05 -.1162 -.1030 -.0873 -.0677 -.0465 -.0406 -.0328 -.0240 -.0145 -.0077 -.0008 0.0055 0.0134 0.0222 0.0316 0.0539 0.0729 0.0888 0.1024
 10 -.1024 -.0944 -.0827 -.0658 -.0450 -.0401 -.0307 -.0224 -.0137 -.0056 0.0015 0.0079 0.0164 0.0251 0.0345 0.0550 0.0719 0.0838 0.0917
 15 -.0799 -.0816 -.0789 -.0608 -.0433 -.0378 -.0286 -.0201 -.0104 -.0037 0.0024 0.0080 0.0159 0.0249 0.0341 0.0513 0.0697 0.0721 0.0683
 20 -.0364 -.0285 -.0304 -.0355 -.0273 -.0233 -.0167 -.0106 -.0056 -.0026 0.0004 0.0045 0.0095 0.0164 0.0229 0.0312 0.0260 0.0242 0.0323
 25 -.0370 -.0163 -.0025 0.0028 -.0087 -.0105 -.0071 -.0049 -.0019 -.0006 0.0004 0.0024 0.0041 0.0055 0.0015 -.0098 -.0050 0.0089 0.0307
 30 -.0169 0.0037 0.0210 0.0303 0.0211 0.0133 0.0096 0.0100 0.0081 0.0043 -.0005 -.0044 -.0078 -.0155 -.0240 -.0318 -.0242 -.0066 0.0139
 35 0.0213 0.0543 0.0602 0.0659 0.0515 0.0439 0.0311 0.0236 0.0178 0.0068 0.0002 -.0047 -.0096 -.0195 -.0275 -.0419 -.0361 -.0298 0.0029
 40 0.0189 0.0463 0.0803 0.0786 0.0519 0.0392 0.0287 0.0209 0.0127 0.0062 -.0017 -.0079 -.0105 -.0161 -.0221 -.0486 -.0497 -.0155 0.0116
 45 0.0055 0.0045 0.0224 0.0432 0.0419 0.0355 0.0274 0.0202 0.0141 0.0069 -.0105 -.0321 -.0375 -.0468 -.0536 -.0549 -.0344 -.0164 -.0174
             </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cn_dr">
        <description>
            coefficient
        </description>
            <table name="table/Cn_dr">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0787 -.0815 -.0741 -.0656 -.0620 -.0627 -.0616 -.0551 -.0520 -.0481 -.0494 -.0486 -.0465 -.0396 -.0310 -.0270 -.0191 -.0113 -.0143
-15 -.0758 -.0745 -.0708 -.0610 -.0623 -.0658 -.0649 -.0580 -.0522 -.0484 -.0465 -.0437 -.0395 -.0298 -.0202 -.0216 -.0117 -.0082 -.0069
-10 -.0850 -.0833 -.0828 -.0749 -.0670 -.0685 -.0657 -.0590 -.0520 -.0476 -.0447 -.0407 -.0338 -.0238 -.0125 -.0046 0.0033 0.0043 0.0056
-05 -.1422 -.1270 -.1170 -.0932 -.0774 -.0745 -.0671 -.0599 -.0522 -.0449 -.0401 -.0337 -.0258 -.0147 -.0045 0.0152 0.0352 0.0498 0.0598
 00 -.1576 -.1381 -.1181 -.0981 -.0791 -.0783 -.0693 -.0610 -.0527 -.0451 -.0389 -.0323 -.0230 -.0116 0.0000 0.0190 0.0389 0.0584 0.0784
 05 -.1591 -.1406 -.1216 -.1026 -.0819 -.0793 -.0696 -.0610 -.0520 -.0450 -.0388 -.0311 -.0220 -.0100 0.0009 0.0215 0.0405 0.0594 0.0794
 10 -.1520 -.1350 -.1170 -.0990 -.0816 -.0779 -.0690 -.0600 -.0513 -.0441 -.0382 -.0309 -.0200 -.0083 0.0031 0.0207 0.0381 0.0550 0.0725
 15 -.1306 -.1091 -.1026 -.0906 -.0752 -.0759 -.0694 -.0605 -.0517 -.0446 -.0386 -.0320 -.0201 -.0088 0.0019 0.0173 0.0289 0.0349 0.0569
 20 -.1271 -.1071 -.0866 -.0836 -.0677 -.0685 -.0676 -.0628 -.0543 -.0475 -.0431 -.0404 -.0321 -.0230 -.0047 0.0012 0.0043 0.0249 0.0447
 25 -.1041 -.0925 -.0738 -.0683 -.0542 -.0600 -.0620 -.0589 -.0527 -.0483 -.0451 -.0411 -.0333 -.0254 -.0179 -.0042 0.0013 0.0197 0.0317
 30 -.0598 -.0295 -.0183 -.0098 -.0049 -.0281 -.0422 -.0475 -.0474 -.0494 -.0510 -.0514 -.0504 -.0437 -.0367 -.0325 -.0242 -.0130 0.0180
 35 -.0467 -.0201 0.0061 0.0186 0.0159 0.0123 -.0085 -.0243 -.0363 -.0449 -.0527 -.0571 -.0607 -.0583 -.0585 -.0611 -.0451 -.0228 0.0104
 40 -.0289 -.0111 0.0386 0.0484 0.0321 0.0145 0.0013 -.0103 -.0243 -.0328 -.0405 -.0449 -.0496 -.0570 -.0659 -.0824 -.0726 -.0227 -.0053
 45 -.0243 -.0129 0.0213 0.0447 0.0325 0.0248 0.0140 0.0047 -.0053 -.0162 -.0410 -.0545 -.0617 -.0697 -.0784 -.0912 -.0672 -.0332 -.0222
 50 -.0395 -.0247 -.0063 0.0177 0.0196 0.0149 0.0082 0.0022 0.0003 -.0081 -.0166 -.0300 -.0438 -.0558 -.0655 -.0632 -.0394 -.0202 -.0058
 55 -.0364 -.0305 0.0088 0.0067 0.0006 -.0018 -.0075 -.0075 0.0004 -.0040 -.0012 -.0089 -.0203 -.0289 -.0318 -.0383 -.0401 -.0011 0.0051
 60 -.0162 -.0127 0.0181 0.0026 -.0084 -.0121 -.0195 -.0193 -.0082 -.0012 0.0066 0.0096 0.0046 -.0033 -.0048 -.0163 -.0317 -.0012 0.0026
 70 0.0267 0.0297 0.0177 0.0069 -.0016 -.0081 -.0156 -.0203 -.0152 -.0015 0.0015 0.0143 0.0157 0.0094 0.0049 -.0035 -.0148 -.0263 -.0236
 80 0.0223 0.0261 0.0215 0.0167 0.0109 0.0084 0.0050 0.0016 -.0002 -.0061 -.0055 -.0089 -.0096 -.0105 -.0114 -.0172 -.0225 -.0268 -.0233
 90 0.0089 0.0077 0.0068 0.0014 -.0036 -.0044 -.0057 -.0010 -.0009 -.0024 -.0042 -.0047 -.0054 -.0058 -.0057 -.0109 -.0157 -.0170 -.0181
            </tableData>
        </table>
    </function>         

    <axis name="YAW">

        <function name="aero/coefficient/Cn">
            <description>
               Cn coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <table name="table/Cn">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">aero/beta-deg</independentVar>
                    <independentVar lookup="table">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                    <tableData breakPoint="-25.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.0885 -0.0687 -0.0582 -0.0421 -0.0164 -0.0080 -0.0056  0.0062  0.0042  0.0000 -0.0038 -0.0136 -0.0107 -0.0044  0.0030  0.0288  0.0448  0.0552  0.0518
-15 -0.0636 -0.0592 -0.0454 -0.0273 -0.0164 -0.0122 -0.0052  0.0002  0.0017  0.0000 -0.0001  0.0021  0.0061  0.0144  0.0191  0.0296  0.0479  0.0622  0.0663
-10 -0.0681 -0.0576 -0.0480 -0.0374 -0.0228 -0.0151 -0.0086 -0.0008  0.0035  0.0000  0.0052  0.0101  0.0166  0.0251  0.0325  0.0473  0.0577  0.0671  0.0774
 -5 -0.0837 -0.0748 -0.0633 -0.0467 -0.0351 -0.0260 -0.0182 -0.0113 -0.0055  0.0000  0.0052  0.0108  0.0183  0.0288  0.0391  0.0507  0.0677  0.0789  0.0874
  0 -0.0979 -0.0857 -0.0807 -0.0516 -0.0366 -0.0271 -0.0185 -0.0113 -0.0050  0.0000  0.0054  0.0119  0.0204  0.0297  0.0388  0.0539  0.0696  0.0885  0.1029
  5 -0.1037 -0.0801 -0.0675 -0.0505 -0.0336 -0.0268 -0.0185 -0.0115 -0.0047  0.0000  0.0055  0.0128  0.0205  0.0293  0.0374  0.0543  0.0711  0.0844  0.1074
 10 -0.0981 -0.0749 -0.0609 -0.0456 -0.0344 -0.0272 -0.0193 -0.0120 -0.0052  0.0000  0.0052  0.0127  0.0221  0.0303  0.0382  0.0495  0.0653  0.0795  0.1024
 15 -0.1017 -0.0625 -0.0460 -0.0431 -0.0330 -0.0259 -0.0172 -0.0112 -0.0043  0.0000  0.0053  0.0126  0.0218  0.0297  0.0364  0.0465  0.0495  0.0653  0.0926
 20 -0.0675 -0.0510 -0.0290 -0.0265 -0.0247 -0.0205 -0.0144 -0.0085 -0.0040  0.0000 -0.0032  0.0009  0.0086  0.0143  0.0189  0.0205  0.0232  0.0455  0.0615
 25 -0.0478 -0.0336 -0.0148 -0.0103 -0.0134 -0.0097 -0.0058 -0.0028 -0.0013  0.0000  0.0008  0.0037  0.0070  0.0111  0.0132  0.0102  0.0142  0.0327  0.0472
 30 -0.0053  0.0193  0.0330  0.0279  0.0345  0.0093  0.0056  0.0035  0.0041  0.0000 -0.0045 -0.0057 -0.0083 -0.0105 -0.0139 -0.0243 -0.0262  0.0052  0.0429
 35 -0.0011  0.0351  0.0617  0.0762  0.0582  0.0586  0.0476  0.0292  0.0164  0.0000 -0.0106 -0.0166 -0.0240 -0.0343 -0.0559 -0.0734 -0.0597 -0.0328  0.0038
 40 -0.0040  0.0195  0.0792  0.0818  0.0590  0.0454  0.0313  0.0197  0.0072  0.0000 -0.0042 -0.0110 -0.0237 -0.0333 -0.0505 -0.0783 -0.0753 -0.0159  0.0048
 45 -0.0122  0.0031  0.0423  0.0568  0.0386  0.0288  0.0177  0.0134  0.0049  0.0000 -0.0122 -0.0351 -0.0438 -0.0584 -0.0699 -0.0913 -0.0748 -0.0359 -0.0207
 50 -0.0402 -0.0309 -0.0135  0.0198  0.0335  0.0312  0.0314  0.0170  0.0111  0.0000 -0.0087 -0.0265 -0.0463 -0.0660 -0.0848 -0.0723 -0.0394 -0.0231 -0.0139
 55 -0.0486 -0.0348  0.0095 -0.0131 -0.0211 -0.0119 -0.0066 -0.0064  0.0039  0.0000 -0.0031 -0.0176 -0.0301 -0.0334 -0.0317 -0.0392 -0.0616 -0.0175 -0.0040
 60 -0.0022  0.0104  0.0415  0.0129  0.0308  0.0184  0.0024 -0.0095 -0.0017  0.0000  0.0046  0.0046 -0.0137 -0.0266 -0.0272 -0.0290 -0.0377 -0.0070  0.0055
 70  0.0216  0.0271  0.0201  0.0136  0.0008 -0.0023 -0.0056 -0.0123 -0.0163  0.0000  0.0025  0.0129  0.0132  0.0075  0.0008 -0.0119 -0.0181 -0.0252 -0.0202
 80  0.0229  0.0209  0.0138  0.0100  0.0091  0.0106  0.0108  0.0089  0.0060  0.0000 -0.0016  0.0029 -0.0059 -0.0069 -0.0049 -0.0061 -0.0097 -0.0180 -0.0187
 90  0.0330  0.0217  0.0106  0.0008  0.0086  0.0067  0.0041  0.0030  0.0018  0.0000 -0.0076 -0.0058 -0.0115 -0.0109 -0.0114 -0.0034 -0.0062 -0.0169 -0.0306
                    </tableData>
                    <tableData breakPoint="0.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
     -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0551 -.0588 -.0496 -.0406 -.0219 -.0145 -.0075 -.0012 0.0002 0.0000 -.0090 0.0012 0.0059 0.0099 0.0141 0.0333 0.0425 0.0516 0.0477
-15 -.0561 -.0527 -.0456 -.0333 -.0248 -.0179 -.0127 -.0057 -.0018 0.0000 0.0025 0.0058 0.0111 0.0180 0.0238 0.0330 0.0450 0.0521 0.0553
-10 -.0666 -.0637 -.0545 -.0468 -.0297 -.0233 -.0145 -.0079 -.0031 0.0000 0.0028 0.0075 0.0150 0.0221 0.0302 0.0474 0.0552 0.0646 0.0674
-05 -.0902 -.0812 -.0664 -.0523 -.0366 -.0277 -.0194 -.0117 -.0055 0.0000 0.0063 0.0127 0.0214 0.0297 0.0398 0.0553 0.0693 0.0843 0.0933
 00 -.1058 -.0916 -.0749 -.0578 -.0413 -.0317 -.0226 -.0138 -.0066 0.0000 0.0061 0.0135 0.0225 0.0324 0.0414 0.0579 0.0746 0.0914 0.1055
 05 -.1074 -.0916 -.0754 -.0587 -.0415 -.0329 -.0227 -.0145 -.0064 0.0000 0.0061 0.0148 0.0231 0.0335 0.0421 0.0594 0.0762 0.0914 0.1079
 10 -.0981 -.0798 -.0718 -.0568 -.0416 -.0326 -.0232 -.0146 -.0062 0.0000 0.0063 0.0147 0.0240 0.0332 0.0427 0.0579 0.0727 0.0809 0.0995
 15 -.0812 -.0592 -.0537 -.0513 -.0375 -.0301 -.0212 -.0121 -.0052 0.0000 0.0063 0.0141 0.0243 0.0334 0.0404 0.0541 0.0566 0.0622 0.0840
 20 -.0684 -.0491 -.0290 -.0321 -.0308 -.0262 -.0179 -.0102 -.0042 0.0000 0.0018 0.0068 0.0152 0.0233 0.0296 0.0309 0.0279 0.0479 0.0674
 25 -.0528 -.0411 -.0223 -.0229 -.0240 -.0188 -.0129 -.0072 -.0029 0.0000 0.0033 0.0088 0.0147 0.0216 0.0258 0.0251 0.0242 0.0429 0.0547
 30 -.0300 0.0002 0.0115 0.0164 0.0091 -.0037 -.0024 0.0090 0.0025 0.0000 -.0029 -.0023 -.0013 -.0030 -.0019 -.0097 -.0042 0.0069 0.0370
 35 -.0098 0.0168 0.0392 0.0514 0.0396 0.0340 0.0163 0.0103 0.0069 0.0000 -.0097 -.0147 -.0157 -.0189 -.0295 -.0415 -.0291 -.0068 0.0194
 40 -.0025 0.0054 0.0683 0.0744 0.0506 0.0351 0.0207 0.0131 0.0052 0.0000 -.0071 -.0136 -.0216 -.0329 -.0440 -.0677 -.0622 0.0012 0.0202
 45 -.0111 0.0010 0.0294 0.0612 0.0451 0.0369 0.0293 0.0201 0.0116 0.0000 -.0237 -.0375 -.0460 -.0565 -.0694 -.0847 -.0530 -.0246 -.0126
 50 -.0256 -.0136 0.0058 0.0287 0.0254 0.0231 0.0233 0.0105 0.0078 0.0000 -.0063 -.0217 -.0355 -.0456 -.0548 -.0574 -.0346 -.0161 -.0046
 55 -.0302 -.0228 0.0130 0.0140 0.0040 0.0027 -.0023 -.0070 0.0043 0.0000 0.0028 -.0058 -.0172 -.0239 -.0258 -.0361 -.0355 0.0014 0.0073
 60 -.0188 -.0075 0.0211 0.0080 -.0061 -.0100 -.0174 -.0219 -.0079 0.0000 0.0075 0.0103 0.0043 -.0013 -.0019 -.0156 -.0284 0.0004 0.0110
 70 0.0296 0.0316 0.0210 0.0092 0.0003 -.0062 -.0128 -.0193 -.0187 0.0000 0.0039 0.0151 0.0163 0.0116 0.0059 -.0023 -.0141 -.0246 -.0228
 80 0.0264 0.0351 0.0254 0.0180 0.0133 0.0126 0.0107 0.0079 0.0055 0.0000 -.0001 0.0060 -.0033 -.0069 -.0075 -.0130 -.0198 -.0242 -.0209
 90 0.0274 0.0128 0.0118 0.0059 0.0051 0.0044 0.0031 0.0027 0.0017 0.0000 -.0018 -.0023 -.0031 -.0048 -.0048 -.0054 -.0111 -.0121 -.0163
                    </tableData>
                    <tableData breakPoint="25.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10     -8      -6      -4      -2       0       2       4       6       8       10      15      20      25      30
-20 -0.0472 -0.0497 -0.0429 -0.0434 -0.0214 -0.0134 -0.0039 -0.0020  0.0001  0.0000  0.0016 -0.0007  0.0045  0.0080  0.0144  0.0362  0.0355  0.0422  0.0412
-15 -0.0484 -0.0447 -0.0389 -0.0322 -0.0189 -0.0148 -0.0087 -0.0022 -0.0012  0.0000  0.0000  0.0024  0.0089  0.0136  0.0184  0.0315  0.0385  0.0444  0.0477
-10 -0.0551 -0.0508 -0.0460 -0.0413 -0.0272 -0.0202 -0.0131 -0.0072 -0.0024  0.0000  0.0016  0.0075  0.0138  0.0222  0.0271  0.0408  0.0457  0.0506  0.0547
 -5 -0.0722 -0.0690 -0.0605 -0.0503 -0.0369 -0.0293 -0.0212 -0.0131 -0.0063  0.0000  0.0064  0.0142  0.0224  0.0306  0.0399  0.0532  0.0633  0.0717  0.0751
  0 -0.0884 -0.0794 -0.0680 -0.0556 -0.0399 -0.0310 -0.0222 -0.0142 -0.0065  0.0000  0.0071  0.0150  0.0231  0.0318  0.0407  0.0562  0.0684  0.0802  0.0891
  5 -0.0807 -0.0707 -0.0635 -0.0517 -0.0404 -0.0320 -0.0222 -0.0123 -0.0043  0.0000  0.0037  0.0118  0.0219  0.0320  0.0414  0.0560  0.0677  0.0754  0.0845
 10 -0.0781 -0.0704 -0.0637 -0.0526 -0.0400 -0.0329 -0.0233 -0.0132 -0.0061  0.0000  0.0046  0.0121  0.0213  0.0305  0.0393  0.0519  0.0630  0.0695  0.0769
 15 -0.0636 -0.0497 -0.0473 -0.0492 -0.0353 -0.0286 -0.0191 -0.0104 -0.0047  0.0000  0.0032  0.0100  0.0199  0.0299  0.0375  0.0502  0.0482  0.0510  0.0645
 20 -0.0327 -0.0321 -0.0224 -0.0275 -0.0312 -0.0272 -0.0184 -0.0088 -0.0033  0.0000  0.0031  0.0048  0.0185  0.0277  0.0341  0.0304  0.0254  0.0348  0.0353
 25 -0.0209 -0.0160 -0.0109 -0.0128 -0.0214 -0.0198 -0.0167 -0.0093 -0.0034  0.0000  0.0046  0.0107  0.0187  0.0276  0.0324  0.0236  0.0220  0.0270  0.0316
 30 -0.0070  0.0177  0.0313  0.0262  0.0116 -0.0073 -0.0073 -0.0048  0.0005  0.0000 -0.0005 -0.0002  0.0026  0.0056  0.0027 -0.0115 -0.0172 -0.0032  0.0213
 35  0.0047  0.0311  0.0526  0.0559  0.0439  0.0393  0.0201  0.0098  0.0069  0.0000 -0.0083 -0.0121 -0.0153 -0.0179 -0.0286 -0.0466 -0.0430 -0.0214  0.0040
 40  0.0010  0.0228  0.0702  0.0799  0.0541  0.0377  0.0263  0.0179  0.0078  0.0000 -0.0087 -0.0150 -0.0256 -0.0370 -0.0490 -0.0747 -0.0646 -0.0068  0.0013
 45 -0.0159 -0.0011  0.0209  0.0558  0.0456  0.0362  0.0287  0.0185  0.0082  0.0000 -0.0256 -0.0410 -0.0524 -0.0635 -0.0717 -0.0793 -0.0468 -0.0247 -0.0227
 50 -0.0210 -0.0184 -0.0111  0.0142  0.0324  0.0326  0.0352  0.0210  0.0131  0.0000 -0.0057 -0.0260 -0.0421 -0.0565 -0.0693 -0.0519 -0.0279 -0.0194 -0.0177
 55 -0.0572 -0.0487 -0.0099 -0.0419 -0.0299 -0.0142 -0.0022 -0.0002  0.0071  0.0000 -0.0040 -0.0092 -0.0236 -0.0262 -0.0241 -0.0124 -0.0441 -0.0056  0.0021
 60 -0.0291 -0.0240  0.0000 -0.0191 -0.0156 -0.0148 -0.0173 -0.0199 -0.0069  0.0000  0.0098  0.0147  0.0073 -0.0032 -0.0087 -0.0051 -0.0247 -0.0011  0.0043
 70  0.0124  0.0259  0.0263  0.0123 -0.0013 -0.0033 -0.0053 -0.0117 -0.0152  0.0000 -0.0059  0.0100  0.0069  0.0076  0.0072 -0.0068 -0.0204 -0.0200 -0.0073
 80  0.0067  0.0140  0.0164  0.0101  0.0068  0.0089  0.0097  0.0082  0.0056  0.0000 -0.0012  0.0038 -0.0046  0.0037 -0.0025 -0.0108 -0.0119 -0.0108 -0.0020
 90  0.0079  0.0094  0.0117  0.0030  0.0062  0.0055  0.0044  0.0037  0.0022  0.0000  0.0002  0.0016  0.0018  0.0002  0.0002  0.0031 -0.0057 -0.0037 -0.0049
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCn_lef">
            <description>
               Cn due to leading edge flaps coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <difference>
                    <p>aero/coefficient/Cn_lef</p>
                    <p>aero/coefficient/Cn_dh0</p>
                </difference>
            </product>
        </function>

        <function name="aero/coefficient/dCn_da-lef">
            <description>
               Cn due to aileron coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <p>fcs/fly-by-wire/roll/aileron-pos-norm</p><!-- 1 = 20 degs -->
                <sum>
                    <difference>
                        <p>aero/coefficient/Cn_da</p>
                        <p>aero/coefficient/Cn_dh0</p>
                    </difference>
                    <product>
                        <p>fcs/fly-by-wire/lef/lef-pos-r-norm</p>
                        <difference>
                            <p>aero/coefficient/Cn_da-lef</p>
                            <p>aero/coefficient/Cn_lef</p>                            
                            <difference>
                                <p>aero/coefficient/Cn_da</p>
                                <p>aero/coefficient/Cn_dh0</p>
                            </difference>
                        </difference>
                    </product>
                </sum>
            </product>
        </function>

        <!--<function name="aero/coefficient/Cn_cg">
            <description>
               Cn due to CoG shift, page 45 of TP 1538
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <v>-1</v>
                <difference>
                    <v>0.35</v>
                    <p>aero/CG-pos-c</p>
                </difference>                    
                <quotient>
                    <property>metrics/cbarw-ft</property>
                    <property>metrics/bw-ft</property>
                </quotient>
                <p>aero/coefficient/Cy_t</p>
            </product>
        </function>-->

        <function name="aero/coefficient/dCn_dr">
            <description>
               Cn due to rudder coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <p>fcs/fly-by-wire/yaw/rudder-pos-norm</p><!-- 1 = 30 degs -->
                <difference>
                    <p>aero/coefficient/Cn_dr</p>
                    <p>aero/coefficient/Cn_dh0</p>
                </difference>
            </product>
        </function>   

        <function name="aero/coefficient/Cn_r">
            <description>
               Cn due to yaw rate coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/r-rad_sec</property>
                <table name="table/Cn_r">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.517
-15 -.517
-10 -.517
-05 -.461
 00 -.414
 05 -.397
 10 -.373
 15 -.455
 20 -.550
 25 -.582
 30 -.595
 35 -.637
 40 -1.02
 45 -.84
 50 -.541
 55 -.35
 60 -.35
 70 -.07
 80 -.15
 90 -.15
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCn_b">
            <description>
               Cn due to beta coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/beta-deg</property>
                <table name="table/dCn_b">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .0
-15 .0
-10 .0
-05 .0
 00 .0
 05 .0
 10 .0
 15 .0
 20 .0
 25 -.0008
 30 .001
 35 .0
 40 .0
 45 .0
 50 .0
 55 .0
 60 .0
 70 .0
 80 .0
 90 .0
                    </tableData>
                </table>
            </product>
        </function>

        <!--<function name="aero/coefficient/dCn_da">
            <description>
               Cn due to aileron coefficient.

               Note: This is not included in equations of motion and is quite insignificant, so ignored.
            </description>
            <product>
                <v>0</v>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>fcs/aileron-pos-rad</property>
                <table name="table/dCn_da">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .0
-15 .0
-10 .0
-05 .0
 00 .0001
 05 .00008
 10 .00016
 15 .00010
 20 .0
 25 .0
 30 .0
 35 .0
 40 .0
 45 .0
 50 .0
 55 .0
 60 .0
 70 .0
 80 .0
 90 .0
                     </tableData>
                </table>
            </product>
        </function>-->

        <function name="aero/coefficient/dCn_r-lef">
            <description>
               Cn due to yaw rate due to leading edge flaps coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/r-rad_sec</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <table name="table/dCn_r-lef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .137
-15 .137
-10 .137
-05 .098
 00 .037
 05 .016
 10 .007
 15 .014
 20 -.103
 25 -.098
 30 -.310
 35 -.437
 40 .167
 45 .084

 50 0.00
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/Cn_p">
            <description>
               Cn due to roll rate coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/p-rad_sec</property>
                <table name="table/Cn_p">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.0006
-15 -.0006
-10 -.0006
-05 .0424
 00 -.0075
 05 -.0214
 10 -.0320
 15 -.0320
 20 .05
 25 .15
 30 .13
 35 .158
 40 .24
 45 .15
 50 0.0
 55 -.2
 60 -.3
 70 .15
 80 0.0
 90 0.0
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCn_p-lef">
            <description>
               Cn due to roll rate due to leading edge flaps coefficient.

               Source for alpha 50+: TN-D-8176
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/p-rad_sec</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <table name="table/dCn_p-lef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .0615
-15 .0615
-10 .0615
-05 .0091
 00 .061
 05 .0129
 10 .0439
 15 .0512
 20 -.0294
 25 .0017
 30 .0584
 35 .211
 40 .392
 45 .196
 50 0.000
 55 0.000
 60 0.000
 70 0.000
 80 0.000
 90 0.000
                     </tableData>
                </table>
            </product>
        </function>

    </axis>














    <function name="aero/coefficient/Cl_dh0">
        <description>
            coefficient
        </description>
            <table name="table/Cl_dh0">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0153 -.0028 0.0091 0.0188 0.0234 0.0173 0.0106 0.0090 0.0041 0.0000 -.0031 -.0064 -.0084 -.0128 -.0171 -.0120 -.0022 0.0097 0.0225
-15 -.0132 -.0028 0.0077 0.0145 0.0104 0.0084 0.0060 0.0039 0.0025 0.0000 -.0029 -.0050 -.0080 -.0086 -.0116 -.0160 -.0090 0.0050 0.0119
-10 -.0102 -.0013 0.0094 0.0134 0.0107 0.0102 0.0081 0.0060 0.0011 0.0000 -.0004 -.0048 -.0071 -.0091 -.0102 -.0135 -.0094 0.0013 0.0108
-05 0.0087 0.0153 0.0186 0.0194 0.0183 0.0156 0.0125 0.0088 0.0043 0.0000 -.0038 -.0087 -.0126 -.0158 -.0186 -.0199 -.0189 -.0157 -.0095
 00 0.0157 0.0190 0.0199 0.0207 0.0185 0.0153 0.0110 0.0071 0.0033 0.0000 -.0030 -.0067 -.0107 -.0147 -.0182 -.0204 -.0196 -.0187 -.0154
 05 0.0318 0.0307 0.0296 0.0272 0.0219 0.0180 0.0132 0.0089 0.0043 0.0000 -.0037 -.0081 -.0126 -.0173 -.0209 -.0263 -.0288 -.0299 -.0310
 10 0.0510 0.0510 0.0496 0.0422 0.0328 0.0271 0.0207 0.0139 0.0056 0.0000 -.0065 -.0137 -.0207 -.0266 -.0322 -.0418 -.0486 -.0501 -.0501
 15 0.0732 0.0679 0.0638 0.0574 0.0433 0.0357 0.0274 0.0187 0.0090 0.0000 -.0088 -.0188 -.0284 -.0369 -.0430 -.0567 -.0624 -.0663 -.0714
 20 0.0895 0.0815 0.0692 0.0579 0.0453 0.0354 0.0270 0.0171 0.0076 0.0000 -.0085 -.0177 -.0271 -.0365 -.0440 -.0569 -.0682 -.0804 -.0884
 25 0.0884 0.0785 0.0665 0.0536 0.0400 0.0326 0.0254 0.0181 0.0081 0.0000 -.0082 -.0165 -.0258 -.0330 -.0403 -.0538 -.0669 -.0788 -.0882
 30 0.0820 0.0505 0.0234 0.0143 0.0064 0.0189 0.0196 0.0133 0.0071 0.0000 -.0057 -.0118 -.0165 -.0205 -.0248 -.0327 -.0418 -.0687 -.1003
 35 0.0790 0.0610 0.0390 0.0095 0.0037 0.0029 0.0150 0.0143 0.0097 0.0000 0.0016 0.0003 -.0018 -.0017 0.0011 -.0034 -.0326 -.0547 -.0726
 40 0.0721 0.0573 0.0302 0.0087 0.0050 0.0104 0.0174 0.0124 0.0062 0.0000 -.0075 -.0108 -.0131 -.0145 -.0148 -.0185 -.0399 -.0671 -.0815
 45 0.0744 0.0576 0.0331 0.0248 0.0170 0.0179 0.0163 0.0191 0.0115 0.0000 -.0042 -.0180 -.0148 -.0156 -.0206 -.0285 -.0364 -.0608 -.0778
 50 0.0534 0.0411 0.0262 0.0238 0.0147 0.0144 0.0130 0.0091 0.0056 0.0000 -.0051 -.0123 -.0152 -.0212 -.0222 -.0313 -.0337 -.0486 -.0609
 55 0.0587 0.0422 0.0320 0.0261 0.0176 0.0151 0.0117 0.0065 0.0045 0.0000 -.0040 -.0081 -.0133 -.0187 -.0201 -.0286 -.0346 -.0488 -.0613
 60 0.0650 0.0481 0.0387 0.0301 0.0229 0.0192 0.0155 0.0094 0.0063 0.0000 -.0029 -.0055 -.0111 -.0163 -.0188 -.0260 -.0346 -.0440 -.0609
 70 0.0663 0.0538 0.0422 0.0307 0.0245 0.0220 0.0160 0.0128 0.0073 0.0000 -.0050 -.0069 -.0120 -.0165 -.0220 -.0282 -.0397 -.0513 -.0638
 80 0.0683 0.0554 0.0430 0.0325 0.0208 0.0149 0.0126 0.0036 0.0045 0.0000 -.0045 -.0086 -.0134 -.0159 -.0186 -.0303 -.0408 -.0532 -.0661
 90 0.0701 0.0534 0.0410 0.0293 0.0205 0.0188 0.0163 0.0110 0.0066 0.0000 0.0000 -.0001 -.0067 -.0124 -.0154 -.0242 -.0359 -.0483 -.0650
             </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cl_lef">
        <description>
            coefficient
        </description>
            <table name="table/Cl_lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0205 -.0170 -.0076 0.0047 0.0150 0.0134 0.0008 0.0013 0.0027 0.0000 -.0012 -.0031 -.0054 -.0051 -.0054 0.0036 0.0159 0.0256 0.0297
-15 -.0060 -.0042 -.0007 0.0033 0.0006 -.0002 0.0022 0.0039 0.0019 0.0000 -.0015 -.0030 -.0039 -.0028 -.0003 -.0024 0.0023 0.0052 0.0072
-10 -.0081 -.0061 -.0001 0.0018 0.0034 0.0022 0.0016 0.0006 0.0000 0.0000 -.0003 -.0008 -.0011 -.0020 -.0026 -.0007 0.0007 0.0071 0.0093
-05 0.0106 0.0102 0.0104 0.0103 0.0093 0.0073 0.0052 0.0030 0.0012 0.0000 -.0010 -.0027 -.0044 -.0065 -.0087 -.0100 -.0103 -.0102 -.0106
 00 0.0238 0.0232 0.0224 0.0240 0.0168 0.0134 0.0098 0.0060 0.0029 0.0000 -.0027 -.0058 -.0094 -.0134 -.0164 -.0200 -.0220 -.0228 -.0234
 05 0.0390 0.0361 0.0353 0.0315 0.0248 0.0202 0.0149 0.0100 0.0049 0.0000 -.0049 -.0100 -.0149 -.0206 -.0250 -.0317 -.0355 -.0363 -.0392
 10 0.0485 0.0463 0.0430 0.0347 0.0263 0.0213 0.0155 0.0100 0.0046 0.0000 -.0048 -.0115 -.0175 -.0227 -.0278 -.0360 -.0443 -.0476 -.0498
 15 0.0462 0.0462 0.0450 0.0420 0.0297 0.0241 0.0172 0.0113 0.0052 0.0000 -.0056 -.0123 -.0187 -.0248 -.0304 -.0369 -.0399 -.0411 -.0411
 20 0.0480 0.0335 0.0290 0.0209 0.0158 0.0141 0.0095 0.0058 0.0005 0.0000 -.0060 -.0117 -.0175 -.0183 -.0203 -.0250 -.0335 -.0378 -.0521
 25 0.0731 0.0573 0.0371 0.0221 0.0233 0.0203 0.0175 0.0120 0.0061 0.0000 -.0058 -.0128 -.0183 -.0186 -.0260 -.0248 -.0398 -.0610 -.0758
 30 0.0752 0.0632 0.0428 0.0235 0.0106 0.0133 0.0138 0.0094 0.0075 0.0000 -.0063 -.0095 -.0110 -.0101 -.0151 -.0280 -.0473 -.0677 -.0797
 35 0.0528 0.0479 0.0422 0.0190 0.0078 0.0069 0.0117 0.0070 0.0022 0.0000 0.0014 -.0057 -.0076 -.0077 -.0091 -.0203 -.0435 -.0492 -.0541
 40 0.0555 0.0435 0.0339 0.0173 0.0094 0.0156 0.0193 0.0110 0.0110 0.0000 -.0074 -.0126 -.0194 -.0213 -.0253 -.0332 -.0498 -.0594 -.0714
 45 0.0500 0.0493 0.0351 0.0306 0.0179 0.0158 0.0128 0.0077 0.0019 0.0000 -.0118 -.0124 -.0150 -.0173 -.0214 -.0341 -.0386 -.0528 -.0535
             </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cl_da">
        <description>
            coefficient
        </description>
            <table name="table/Cl_da">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0499 -.0325 -.0184 -.0113 -.0023 -.0059 -.0125 -.0116 -.0170 -.0211 -.0242 -.0271 -.0331 -.0352 -.0392 -.0302 -.0231 -.0090 0.0084
-15 -.0476 -.0346 -.0215 -.0132 -.0180 -.0211 -.0246 -.0248 -.0284 -.0311 -.0320 -.0341 -.0366 -.0349 -.0386 -.0434 -.0351 -.0220 -.0090
-10 -.0452 -.0339 -.0272 -.0245 -.0250 -.0259 -.0267 -.0292 -.0337 -.0325 -.0327 -.0349 -.0371 -.0401 -.0433 -.0438 -.0411 -.0344 -.0231
-05 -.0344 -.0303 -.0258 -.0230 -.0242 -.0270 -.0301 -.0334 -.0368 -.0402 -.0440 -.0480 -.0511 -.0541 -.0555 -.0567 -.0539 -.0494 -.0453
 00 -.0404 -.0372 -.0327 -.0302 -.0323 -.0342 -.0373 -.0414 -.0451 -.0482 -.0510 -.0536 -.0570 -.0595 -.0624 -.0645 -.0620 -.0575 -.0543
 05 -.0251 -.0256 -.0241 -.0252 -.0297 -.0334 -.0378 -.0425 -.0472 -.0517 -.0554 -.0586 -.0618 -.0653 -.0685 -.0730 -.0741 -.0726 -.0731
 10 -.0031 -.0026 -.0027 -.0091 -.0185 -.0235 -.0301 -.0366 -.0437 -.0501 -.0557 -.0608 -.0665 -.0717 -.0771 -.0865 -.0929 -.0930 -.0925
 15 0.0158 0.0145 0.0121 0.0063 -.0068 -.0135 -.0214 -.0313 -.0401 -.0492 -.0576 -.0656 -.0729 -.0780 -.0855 -.0986 -.1044 -.1068 -.1081
 20 0.0074 0.0045 0.0038 0.0063 0.0026 -.0053 -.0137 -.0228 -.0322 -.0416 -.0515 -.0606 -.0689 -.0784 -.0863 -.0900 -.0875 -.0882 -.0911
 25 0.0296 0.0258 0.0237 0.0157 0.0046 -.0025 -.0105 -.0202 -.0287 -.0374 -.0454 -.0536 -.0617 -.0686 -.0763 -.0874 -.0954 -.0975 -.1013
 30 0.0404 0.0081 -.0149 -.0074 -.0196 -.0105 -.0122 -.0193 -.0244 -.0306 -.0362 -.0429 -.0456 -.0493 -.0501 -.0623 -.0548 -.0778 -.1101
 35 0.0309 0.0126 0.0020 -.0246 -.0223 -.0246 -.0172 -.0215 -.0275 -.0358 -.0354 -.0373 -.0361 -.0343 -.0324 -.0301 -.0567 -.0673 -.0856
 40 0.0419 0.0253 0.0041 -.0183 -.0154 -.0061 -.0014 -.0057 -.0117 -.0195 -.0276 -.0310 -.0347 -.0346 -.0339 -.0310 -.0534 -.0746 -.0912
 45 0.0579 0.0418 0.0181 0.0110 0.0035 0.0019 .00000 -.0010 -.0018 -.0116 -.0170 -.0198 -.0243 -.0236 -.0311 -.0386 -.0457 -.0694 -.0855
 50 0.0415 0.0304 0.0210 0.0194 0.0072 0.0061 0.0046 0.0007 -.0017 -.0069 -.0129 -.0218 -.0249 -.0302 -.0297 -.0419 -.0435 -.0529 -.0640
 55 0.0467 0.0291 0.0239 0.0180 0.0083 0.0054 0.0013 -.0026 -.0048 -.0100 -.0143 -.0204 -.0237 -.0283 -.0296 -.0393 -.0452 -.0504 -.0680
 60 0.0490 0.0323 0.0267 0.0182 0.0089 0.0046 -.0005 -.0043 -.0070 -.0119 -.0155 -.0193 -.0235 -.0277 -.0296 -.0389 -.0474 -.0530 -.0697
 70 0.0405 0.0396 0.0286 0.0184 0.0070 0.0070 -.0035 -.0060 -.0067 -.0088 -.0146 -.0156 -.0207 -.0250 -.0270 -.0384 -.0486 -.0596 -.0685
 80 0.0616 0.0483 0.0387 0.0293 0.0161 0.0127 0.0091 0.0048 0.0027 -.0023 -.0069 -.0136 -.0140 -.0185 -.0225 -.0357 -.0451 -.0547 -.0680
 90 0.0706 0.0522 0.0400 0.0317 0.0182 0.0143 0.0105 0.0076 0.0037 0.0012 -.0035 -.0062 -.0100 -.0133 -.0170 -.0305 -.0388 -.0510 -.0694
            </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cl_da-lef">
        <description>
            coefficient
        </description>
            <table name="table/Cl_da-lef">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0522 -.0388 -.0295 -.0190 -.0133 -.0214 -.0230 -.0214 -.0213 -.0219 -.0217 -.0242 -.0274 -.0289 -.0304 -.0245 -.0137 -.0038 0.0101
-15 -.0462 -.0450 -.0440 -.0419 -.0373 -.0351 -.0328 -.0283 -.0284 -.0307 -.0324 -.0328 -.0339 -.0348 -.0357 -.0313 -.0284 -.0272 -.0253
-10 -.0487 -.0476 -.0407 -.0409 -.0382 -.0361 -.0375 -.0380 -.0391 -.0399 -.0403 -.0406 -.0412 -.0439 -.0446 -.0427 -.0425 -.0347 -.0336
-05 -.0419 -.0447 -.0428 -.0407 -.0446 -.0458 -.0469 -.0493 -.0508 -.0524 -.0533 -.0537 -.0550 -.0566 -.0578 -.0614 -.0591 -.0579 -.0603
 00 -.0295 -.0292 -.0307 -.0313 -.0354 -.0387 -.0410 -.0450 -.0486 -.0512 -.0541 -.0568 -.0599 -.0623 -.0651 -.0696 -.0699 -.0707 -.0704
 05 -.0165 -.0188 -.0174 -.0204 -.0271 -.0316 -.0364 -.0414 -.0474 -.0527 -.0574 -.0618 -.0661 -.0705 -.0750 -.0819 -.0840 -.0841 -.0858
 10 0.0048 0.0017 -.0026 -.0198 -.0179 -.0221 -.0277 -.0329 -.0389 -.0432 -.0479 -.0529 -.0576 -.0625 -.0674 -.0759 -.0830 -.0872 -.0901
 15 -.0069 -.0068 -.0063 -.0089 -.0156 -.0195 -.0265 -.0321 -.0378 -.0447 -.0489 -.0526 -.0584 -.0643 -.0699 -.0761 -.0795 -.0787 -.0783
 20 0.0156 0.0048 0.0053 0.0037 -.0065 -.0075 -.0100 -.0148 -.0190 -.0229 -.0282 -.0345 -.0369 -.0405 -.0415 -.0516 -.0527 -.0521 -.0634
 25 0.0308 0.0244 0.0078 -.0102 -.0021 -.0006 -.0086 -.0144 -.0196 -.0261 -.0306 -.0369 -.0417 -.0441 -.0464 -.0386 -.0485 -.0657 -.0820
 30 0.0380 0.0302 0.0149 0.0016 -.0080 -.0039 -.0111 -.0148 -.0212 -.0238 -.0333 -.0372 -.0376 -.0354 -.0357 -.0458 -.0589 -.0742 -.0817
 35 0.0232 0.0189 0.0168 -.0049 -.0121 -.0153 -.0107 -.0166 -.0238 -.0263 -.0301 -.0318 -.0357 -.0356 -.0354 -.0429 -.0644 -.0665 -.0707
 40 0.0436 0.0345 0.0217 0.0087 0.0033 0.0121 0.0088 0.0090 0.0071 -.0080 -.0097 -.0210 -.0288 -.0347 -.0351 -.0405 -.0534 -.0665 -.0754
 45 0.0499 0.0450 0.0350 0.0263 0.0128 0.0097 0.0089 0.0058 0.0002 -.0059 -.0096 -.0168 -.0172 -.0232 -.0233 -.0378 -.0460 -.0560 -.0599
             </tableData>
        </table>
    </function>

    <function name="aero/coefficient/Cl_dr">
        <description>
            coefficient
        </description>
            <table name="table/Cl_dr">
                <independentVar lookup="row">aero/alpha-deg</independentVar>
                <independentVar lookup="column">aero/beta-deg</independentVar>
                <tableData note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0100 0.0057 0.0178 0.0291 0.0365 0.0364 0.0336 0.0316 0.0251 0.0216 0.0159 0.0154 0.0142 0.0100 0.0005 0.0079 0.0191 0.0311 0.0465
-15 -.0062 0.0064 0.0192 0.0249 0.0258 0.0263 0.0271 0.0243 0.0213 0.0192 0.0168 0.0149 0.0121 0.0109 0.0066 0.0076 0.0150 0.0275 0.0440
-10 -.0054 0.0058 0.0172 0.0212 0.0240 0.0255 0.0268 0.0246 0.0205 0.0187 0.0172 0.0131 0.0113 0.0098 0.0047 0.0076 0.0115 0.0230 0.0343
-05 0.0260 0.0316 0.0342 0.0330 0.0310 0.0311 0.0289 0.0252 0.0204 0.0153 0.0111 0.0072 0.0031 -.0010 -.0047 -.0068 -.0079 -.0050 0.0006
 00 0.0291 0.0328 0.0338 0.0329 0.0293 0.0298 0.0261 0.0220 0.0181 0.0145 0.0111 0.0078 0.0035 -.0010 -.0054 -.0087 -.0093 -.0080 -.0044
 05 0.0410 0.0430 0.0430 0.0394 0.0330 0.0314 0.0271 0.0230 0.0183 0.0138 0.0097 0.0056 0.0008 -.0045 -.0087 -.0152 -.0183 -.0183 -.0205
 10 0.0638 0.0638 0.0624 0.0550 0.0440 0.0399 0.0341 0.0278 0.0207 0.0135 0.0071 0.0004 -.0071 -.0138 -.0201 -.0309 -.0383 -.0397 -.0397
 15 0.0820 0.0770 0.0730 0.0653 0.0518 0.0481 0.0410 0.0328 0.0227 0.0134 0.0046 -.0045 -.0143 -.0239 -.0320 -.0454 -.0530 -.0570 -.0620
 20 0.1090 0.0930 0.0810 0.0710 0.0532 0.0476 0.0414 0.0315 0.0227 0.0139 0.0058 -.0030 -.0120 -.0231 -.0324 -.0501 -.0598 -.0719 -.0799
 25 0.0930 0.0836 0.0716 0.0609 0.0447 0.0425 0.0367 0.0307 0.0228 0.0145 0.0049 -.0032 -.0118 -.0212 -.0302 -.0466 -.0571 -.0690 -.0784
 30 0.0820 0.0505 0.0236 0.0170 0.0047 0.0242 0.0271 0.0246 0.0215 0.0128 0.0082 0.0012 -.0052 -.0092 -.0165 -.0291 -.0358 -.0625 -.0939
 35 0.0640 0.0550 0.0330 0.0033 -.0018 -.0037 0.0099 0.0121 0.0076 0.0012 0.0007 0.0000 -.0010 -.0015 -.0033 -.0085 -.0379 -.0600 -.0690
 40 0.0584 0.0577 0.0360 0.0088 0.0047 0.0092 0.0143 0.0140 0.0129 0.0030 -.0006 -.0053 -.0073 -.0088 -.0110 -.0143 -.0426 -.0641 -.0648
 45 0.0825 0.0635 0.0405 0.0319 0.0229 0.0200 0.0229 0.0236 0.0139 0.0013 0.0017 -.0056 -.0091 -.0109 -.0174 -.0263 -.0349 -.0578 -.0771
 50 0.0536 0.0446 0.0302 0.0250 0.0164 0.0162 0.0156 0.0124 0.0087 0.0033 -.0035 -.0074 -.0137 -.0143 -.0195 -.0279 -.0332 -.0479 -.0570
 55 0.0580 0.0430 0.0325 0.0260 0.0161 0.0143 0.0120 0.0081 0.0064 0.0014 -.0039 -.0069 -.0138 -.0161 -.0194 -.0281 -.0347 -.0454 -.0600
 60 0.0600 0.0448 0.0350 0.0270 0.0182 0.0157 0.0130 0.0077 0.0048 -.0012 -.0055 -.0078 -.0140 -.0172 -.0202 -.0290 -.0375 -.0470 -.0624
 70 0.0656 0.0550 0.0440 0.0330 0.0229 0.0206 0.0162 0.0112 0.0039 -.0005 -.0023 -.0077 -.0125 -.0165 -.0209 -.0308 -.0420 -.0529 -.0636
 80 0.0680 0.0570 0.0450 0.0341 0.0219 0.0183 0.0116 0.0118 0.0063 -.0005 -.0045 -.0065 -.0108 -.0162 -.0173 -.0292 -.0401 -.0522 -.0634
 90 0.0660 0.0532 0.0390 0.0269 0.0174 0.0156 0.0102 0.0089 0.0069 0.0008 -.0030 -.0051 -.0074 -.0132 -.0156 -.0247 -.0368 -.0513 -.0638
            </tableData>
        </table>
    </function>
                    
    <axis name="ROLL">

        <function name="aero/coefficient/Cl">
            <description>
               Cl coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <table name="table/Cl">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <independentVar lookup="column">aero/beta-deg</independentVar>
                    <independentVar lookup="table">fcs/fly-by-wire/pitch/horz-tail-deflection-deg</independentVar>
                    <tableData breakPoint="-25.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10      -8      -6      -4      -2      0       2       4       6       8      10      15      20      25      30
-20 -0.0572  0.0088  0.0144  0.0224  0.0277  0.0254  0.0247  0.0201  0.0141  0.0000 -0.0112 -0.0193 -0.0242 -0.0267 -0.0264 -0.0215 -0.0128 -0.0073 -0.0204
-15 -0.0027  0.0081  0.0203  0.0266  0.0208  0.0175  0.0148  0.0123  0.0070  0.0000 -0.0067 -0.0114 -0.0163 -0.0181 -0.0207 -0.0266 -0.0201 -0.0088  0.0030
-10 -0.0016  0.0122  0.0193  0.0197  0.0133  0.0100  0.0090  0.0055  0.0031  0.0000 -0.0058 -0.0084 -0.0130 -0.0147 -0.0172 -0.0241 -0.0152 -0.0078  0.0059
 -5  0.0351  0.0268  0.0245  0.0215  0.0177  0.0141  0.0110  0.0068  0.0027  0.0000 -0.0039 -0.0080 -0.0122 -0.0147 -0.0189 -0.0227 -0.0254 -0.0277 -0.0238
  0  0.0306  0.0309  0.0278  0.0230  0.0190  0.0151  0.0113  0.0076  0.0036  0.0000 -0.0036 -0.0077 -0.0116 -0.0152 -0.0188 -0.0228 -0.0276 -0.0307 -0.0304
  5  0.0408  0.0345  0.0414  0.0285  0.0245  0.0199  0.0145  0.0098  0.0051  0.0000 -0.0050 -0.0097 -0.0141 -0.0192 -0.0235 -0.0299 -0.0352 -0.0362 -0.0420
 10  0.0575  0.0570  0.0551  0.0463  0.0351  0.0289  0.0221  0.0149  0.0070  0.0000 -0.0069 -0.0145 -0.0222 -0.0286 -0.0348 -0.0454 -0.0542 -0.0557 -0.0562
 15  0.0738  0.0668  0.0627  0.0567  0.0441  0.0362  0.0272  0.0185  0.0091  0.0000 -0.0087 -0.0182 -0.0287 -0.0367 -0.0434 -0.0568 -0.0627 -0.0674 -0.0742
 20  0.0728  0.0681  0.0645  0.0544  0.0454  0.0383  0.0288  0.0189  0.0097  0.0000 -0.0105 -0.0181 -0.0299 -0.0370 -0.0450 -0.0535 -0.0632 -0.0667 -0.0708
 25  0.0917  0.0695  0.0618  0.0507  0.0396  0.0332  0.0263  0.0174  0.0080  0.0000 -0.0091 -0.0176 -0.0264 -0.0351 -0.0413 -0.0522 -0.0629 -0.0708 -0.0776
 30  0.0724  0.0410  0.0068  0.0102  0.0015  0.0143  0.0176  0.0124  0.0096  0.0000 -0.0068 -0.0126 -0.0159 -0.0191 -0.0219 -0.0303 -0.0333 -0.0613 -0.0928
 35  0.0683  0.0510  0.0469  0.0206  0.0075 -0.0032 -0.0059 -0.0001 -0.0038  0.0000  0.0019  0.0011  0.0001  0.0042  0.0122 -0.0013 -0.0270 -0.0311 -0.0485
 40  0.0651  0.0613  0.0366  0.0143  0.0084  0.0089  0.0152  0.0089  0.0045  0.0000 -0.0078 -0.0119 -0.0121 -0.0151 -0.0126 -0.0179 -0.0404 -0.0652 -0.0691
 45  0.0799  0.0560  0.0347  0.0231  0.0145  0.0130  0.0073  0.0064  0.0018  0.0000 -0.0055 -0.0058 -0.0118 -0.0130 -0.0171 -0.0271 -0.0372 -0.0572 -0.0811
 50  0.0623  0.0607  0.0521  0.0366  0.0175  0.0147  0.0129  0.0089  0.0055  0.0000 -0.0015 -0.0051 -0.0075 -0.0160 -0.0195 -0.0386 -0.0541 -0.0627 -0.0643
 55  0.0420  0.0298  0.0241  0.0110 -0.0048 -0.0008  0.0023  0.0015  0.0020  0.0000 -0.0070 -0.0142 -0.0187 -0.0303 -0.0166 -0.0324 -0.0455 -0.0502 -0.0633
 60  0.0600  0.0396  0.0323  0.0212  0.0114  0.0105  0.0094  0.0057  0.0044  0.0000 -0.0025 -0.0048 -0.0091 -0.0124 -0.0129 -0.0228 -0.0339 -0.0411 -0.0615
 70  0.0726  0.0619  0.0521  0.0162  0.0215  0.0183  0.0115  0.0089  0.0053  0.0000 -0.0070 -0.0110 -0.0149 -0.0150 -0.0160 -0.0295 -0.0483 -0.0582 -0.0688
 80  0.0597  0.0495  0.0399  0.0305  0.0201  0.0172  0.0177  0.0089  0.0073  0.0000 -0.0038 -0.0072 -0.0122 -0.0155 -0.0191 -0.0296 -0.0389 -0.0486 -0.0587
 90  0.0576  0.0442  0.0351  0.0243  0.0215  0.0182  0.0143  0.0086  0.0054  0.0000 -0.0008 -0.0015 -0.0091 -0.0159 -0.0200 -0.0228 -0.0337 -0.0427 -0.0561
                    </tableData>
                    <tableData breakPoint="0.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30    -25    -20    -15    -10    -8     -6     -4     -2      0      2      4      6      8      10     15     20     25     30
-20 -.0153 -.0028 0.0091 0.0188 0.0234 0.0173 0.0106 0.0090 0.0041 0.0000 -.0031 -.0064 -.0084 -.0128 -.0171 -.0120 -.0022 0.0097 0.0225
-15 -.0132 -.0028 0.0077 0.0145 0.0104 0.0084 0.0060 0.0039 0.0025 0.0000 -.0029 -.0050 -.0080 -.0086 -.0116 -.0160 -.0090 0.0050 0.0119
-10 -.0102 -.0013 0.0094 0.0134 0.0107 0.0102 0.0081 0.0060 0.0011 0.0000 -.0004 -.0048 -.0071 -.0091 -.0102 -.0135 -.0094 0.0013 0.0108
-05 0.0087 0.0153 0.0186 0.0194 0.0183 0.0156 0.0125 0.0088 0.0043 0.0000 -.0038 -.0087 -.0126 -.0158 -.0186 -.0199 -.0189 -.0157 -.0095
 00 0.0157 0.0190 0.0199 0.0207 0.0185 0.0153 0.0110 0.0071 0.0033 0.0000 -.0030 -.0067 -.0107 -.0147 -.0182 -.0204 -.0196 -.0187 -.0154
 05 0.0318 0.0307 0.0296 0.0272 0.0219 0.0180 0.0132 0.0089 0.0043 0.0000 -.0037 -.0081 -.0126 -.0173 -.0209 -.0263 -.0288 -.0299 -.0310
 10 0.0510 0.0510 0.0496 0.0422 0.0328 0.0271 0.0207 0.0139 0.0056 0.0000 -.0065 -.0137 -.0207 -.0266 -.0322 -.0418 -.0486 -.0501 -.0501
 15 0.0732 0.0679 0.0638 0.0574 0.0433 0.0357 0.0274 0.0187 0.0090 0.0000 -.0088 -.0188 -.0284 -.0369 -.0430 -.0567 -.0624 -.0663 -.0714
 20 0.0895 0.0815 0.0692 0.0579 0.0453 0.0354 0.0270 0.0171 0.0076 0.0000 -.0085 -.0177 -.0271 -.0365 -.0440 -.0569 -.0682 -.0804 -.0884
 25 0.0884 0.0785 0.0665 0.0536 0.0400 0.0326 0.0254 0.0181 0.0081 0.0000 -.0082 -.0165 -.0258 -.0330 -.0403 -.0538 -.0669 -.0788 -.0882
 30 0.0820 0.0505 0.0234 0.0143 0.0064 0.0189 0.0196 0.0133 0.0071 0.0000 -.0057 -.0118 -.0165 -.0205 -.0248 -.0327 -.0418 -.0687 -.1003
 35 0.0790 0.0610 0.0390 0.0095 0.0037 0.0029 0.0150 0.0143 0.0097 0.0000 0.0016 0.0003 -.0018 -.0017 0.0011 -.0034 -.0326 -.0547 -.0726
 40 0.0721 0.0573 0.0302 0.0087 0.0050 0.0104 0.0174 0.0124 0.0062 0.0000 -.0075 -.0108 -.0131 -.0145 -.0148 -.0185 -.0399 -.0671 -.0815
 45 0.0744 0.0576 0.0331 0.0248 0.0170 0.0179 0.0163 0.0191 0.0115 0.0000 -.0042 -.0180 -.0148 -.0156 -.0206 -.0285 -.0364 -.0608 -.0778
 50 0.0534 0.0411 0.0262 0.0238 0.0147 0.0144 0.0130 0.0091 0.0056 0.0000 -.0051 -.0123 -.0152 -.0212 -.0222 -.0313 -.0337 -.0486 -.0609
 55 0.0587 0.0422 0.0320 0.0261 0.0176 0.0151 0.0117 0.0065 0.0045 0.0000 -.0040 -.0081 -.0133 -.0187 -.0201 -.0286 -.0346 -.0488 -.0613
 60 0.0650 0.0481 0.0387 0.0301 0.0229 0.0192 0.0155 0.0094 0.0063 0.0000 -.0029 -.0055 -.0111 -.0163 -.0188 -.0260 -.0346 -.0440 -.0609
 70 0.0663 0.0538 0.0422 0.0307 0.0245 0.0220 0.0160 0.0128 0.0073 0.0000 -.0050 -.0069 -.0120 -.0165 -.0220 -.0282 -.0397 -.0513 -.0638
 80 0.0683 0.0554 0.0430 0.0325 0.0208 0.0149 0.0126 0.0036 0.0045 0.0000 -.0045 -.0086 -.0134 -.0159 -.0186 -.0303 -.0408 -.0532 -.0661
 90 0.0701 0.0534 0.0410 0.0293 0.0205 0.0188 0.0163 0.0110 0.0066 0.0000 0.0000 -.0001 -.0067 -.0124 -.0154 -.0242 -.0359 -.0483 -.0650
                    </tableData>
                    <tableData breakPoint="25.0" note="Numbers in this table typed in by E.V.Oort and L.Sonneveldt">
    -30     -25     -20     -15     -10      -8      -6      -4      -2      0       2       4       6       8      10      15      20      25      30
-20 -0.0134 -0.0106  0.0110  0.0237  0.0252  0.0138  0.0114  0.0040  0.0029  0.0000 -0.0034 -0.0085 -0.0075 -0.0168 -0.0190 -0.0179 -0.0050 -0.0117 -0.0376
-15 -0.0043  0.0048  0.0156  0.0225  0.0170  0.0110  0.0068  0.0065  0.0028  0.0000 -0.0023 -0.0049 -0.0074 -0.0091 -0.0139 -0.0189 -0.0131 -0.0034  0.0072
-10  0.0026  0.0096  0.0140  0.0155  0.0147  0.0110  0.0090  0.0028  0.0007  0.0000 -0.0007 -0.0052 -0.0077 -0.0097 -0.0137 -0.0141 -0.0130 -0.0085 -0.0017
 -5  0.0192  0.0207  0.0186  0.0207  0.0181  0.0139  0.0108  0.0079  0.0038  0.0000 -0.0034 -0.0067 -0.0105 -0.0137 -0.0172 -0.0204 -0.0183 -0.0203 -0.0194
  0  0.0295  0.0279  0.0257  0.0217  0.0189  0.0146  0.0104  0.0055  0.0024  0.0000 -0.0029 -0.0065 -0.0108 -0.0153 -0.0190 -0.0218 -0.0260 -0.0282 -0.0298
  5  0.0454  0.0393  0.0370  0.0288  0.0220  0.0180  0.0140  0.0102  0.0071  0.0000 -0.0067 -0.0119 -0.0147 -0.0189 -0.0233 -0.0301 -0.0376 -0.0398 -0.0454
 10  0.0650  0.0618  0.0565  0.0462  0.0332  0.0265  0.0208  0.0148  0.0079  0.0000 -0.0068 -0.0163 -0.0225 -0.0272 -0.0335 -0.0447 -0.0546 -0.0591 -0.0621
 15  0.0787  0.0700  0.0619  0.0537  0.0436  0.0376  0.0310  0.0220  0.0118  0.0000 -0.0116 -0.0227 -0.0308 -0.0382 -0.0460 -0.0558 -0.0640 -0.0719 -0.0800
 20  0.0814  0.0789  0.0695  0.0553  0.0421  0.0327  0.0236  0.0172  0.0080  0.0000 -0.0106 -0.0208 -0.0201 -0.0276 -0.0383 -0.0508 -0.0646 -0.0740 -0.0759
 25  0.0894  0.0754  0.0628  0.0521  0.0283  0.0186  0.0154  0.0125  0.0056  0.0000 -0.0076 -0.0136 -0.0188 -0.0194 -0.0246 -0.0482 -0.0589 -0.0718 -0.0860
 30  0.0784  0.0439  0.0184  0.0016 -0.0074  0.0093  0.0087  0.0043  0.0021  0.0000 -0.0033 -0.0061 -0.0093 -0.0109 -0.0133 -0.0220 -0.0384 -0.0640 -0.0986
 35  0.0741  0.0551  0.0338  0.0065 -0.0047 -0.0104 -0.0040  0.0071 -0.0004  0.0000 -0.0009 -0.0008  0.0011  0.0041  0.0105 -0.0008 -0.0282 -0.0492 -0.0682
 40  0.0661  0.0586  0.0296  0.0041 -0.0015  0.0013  0.0089  0.0035  0.0053  0.0000 -0.0049 -0.0069 -0.0091 -0.0036 -0.0048 -0.0104 -0.0359 -0.0650 -0.0723
 45  0.0787  0.0637  0.0431  0.0346  0.0191  0.0159  0.0136  0.0159  0.0115  0.0000 -0.0016 -0.0054 -0.0094 -0.0129 -0.0135 -0.0289 -0.0378 -0.0583 -0.0728
 50  0.0640  0.0546  0.0426  0.0348  0.0203  0.0110  0.0156  0.0106  0.0064  0.0000 -0.0046 -0.0113 -0.0151 -0.0235 -0.0267 -0.0412 -0.0490 -0.0610 -0.0704
 55  0.0448  0.0315  0.0243  0.0121 -0.0024  0.0019  0.0053  0.0041  0.0033  0.0000 -0.0088 -0.0176 -0.0236 -0.0258 -0.0240 -0.0385 -0.0506 -0.0568 -0.0712
 60  0.0601  0.0415  0.0305  0.0254  0.0217  0.0158  0.0163  0.0104  0.0073  0.0000 -0.0045 -0.0088 -0.0150 -0.0197 -0.0217 -0.0254 -0.0305 -0.0415 -0.0602
 70  0.0652  0.0493  0.0342  0.0203  0.0170  0.0164  0.0123  0.0108  0.0062  0.0000 -0.0068 -0.0104 -0.0153 -0.0185 -0.0206 -0.0292 -0.0431 -0.0582 -0.0741
 80  0.0627  0.0494  0.0368  0.0278  0.0172  0.0135  0.0136  0.0054  0.0054  0.0000 -0.0024 -0.0044 -0.0093 -0.0144 -0.0196 -0.0302 -0.0392 -0.0518 -0.0651
 90  0.0584  0.0474  0.0406  0.0308  0.0213  0.0178  0.0166  0.0118  0.0071  0.0000 -0.0010 -0.0021 -0.0231 -0.0132 -0.0149 -0.0245 -0.0343 -0.0411 -0.0520
                     </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCl_lef">
            <description>
               Cl due to leading edge flaps coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <difference>
                    <p>aero/coefficient/Cl_lef</p>
                    <p>aero/coefficient/Cl_dh0</p>
                </difference>
            </product>
        </function>

        <function name="aero/coefficient/dCl_da">
            <description>
               Cl due to aileron coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <p>fcs/fly-by-wire/roll/aileron-pos-norm</p>
                <difference>
                    <p>aero/coefficient/Cl_da</p>
                    <p>aero/coefficient/Cl_dh0</p>
                </difference>
            </product>
        </function>

        <function name="aero/coefficient/dCl_da-lef">
            <description>
               Cl due to aileron coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <p>fcs/fly-by-wire/roll/aileron-pos-norm</p>
                <p>fcs/fly-by-wire/lef/lef-pos-r-norm</p>
                <difference>
                    <p>aero/coefficient/Cl_da-lef</p>
                    <p>aero/coefficient/Cl_lef</p>                            
                    <difference>
                        <p>aero/coefficient/Cl_da</p>
                        <p>aero/coefficient/Cl_dh0</p>
                    </difference>
                </difference>
            </product>
        </function>

        <function name="aero/coefficient/dCl_dr">
            <description>
               Cl due to rudder coefficient
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <p>fcs/fly-by-wire/yaw/rudder-pos-norm</p>
                <difference>
                    <p>aero/coefficient/Cl_dr</p>
                    <p>aero/coefficient/Cl_dh0</p>
                </difference>
            </product>
        </function>   

        <function name="aero/coefficient/Cl_r">
            <description>
               Cl due to yaw rate coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/r-rad_sec</property>
                <table name="table/Cl_r">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.155
-15 -.155
-10 -.155
-05 -.201
 00 -.0024
 05 .088
 10 .205
 15 .22
 20 .319
 25 .437
 30 .68
 35 .1
 40 .447
 45 -.33
 50 -.068
 55 .118
 60 .0802
 70 .0529
 80 .0868
 90 -.0183
                    </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCl_b">
            <description>
               Cl due to beta coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/beta-deg</property>
                <table name="table/dCl_b">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .0
-15 .0
-10 .0
-05 .0
 00 .0
 05 .0
 10 .0
 15 .0007
 20 .0005
 25 .0003
 30 .0
 35 .0
 40 .0
 45 .0
 50 .0
 55 .0
 60 .0
 70 .0
 80 .0
 90 .0
                    </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCl_r-lef">
            <description>
               Cl due to yaw rate due to leading edge flaps coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/r-rad_sec</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <table name="table/dCl_r-lef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .029
-15 .029
-10 .029
-05 .175
 00 .665
 05 .036
 10 .007
 15 .066
 20 .201
 25 .006
 30 -.068
 35 -.537
 40 -.787
 45 -.394
                    </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/Cl_p">
            <description>
               Cl due to roll rate coefficient.
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/p-rad_sec</property>
                <table name="table/Cl_p">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 -.366
-15 -.366
-10 -.366
-05 -.377
 00 -.345
 05 -.434
 10 -.408
 15 -.388
 20 -.329
 25 -.294
 30 -.23
 35 -.21
 40 -.12
 45 -.10
 50 -.1
 55 -.12
 60 -.14
 70 -.1
 80 -.15
 90 -.2
                    </tableData>
                </table>
            </product>
        </function>

        <function name="aero/coefficient/dCl_p-lef">
            <description>
               Cl due to roll rate due to leading edge flaps coefficient.

               Source for alpha 50+: TN-D-8176
            </description>
            <product>
                <property>aero/qbar-psf</property>
                <property>metrics/Sw-sqft</property>
                <property>metrics/bw-ft</property>
                <property>aero/bi2vel</property>
                <property>velocities/p-rad_sec</property>
                <property>fcs/fly-by-wire/lef/lef-pos-r-norm</property>
                <table name="table/dCl_p-lef">
                    <independentVar lookup="row">aero/alpha-deg</independentVar>
                    <tableData>
-20 .006
-15 .006
-10 .006
-05 .018
 00 -.1
 05 .02
 10 .058
 15 .087
 20 .027
 25 -.056
 30 -.082
 35 .362
 40 .194
 45 .097
 50 0.000
 55 0.000
 60 0.000
 70 0.000
 80 0.000
 90 0.000
                    </tableData>
                </table>
            </product>
        </function>                        

    </axis>

</aerodynamics>
<!--
<output name="c:/users/nikolai/documents/f16_datalog.csv" type="CSV" rate="120">
 <property> fcs/fly-by-wire/pitch/q-washout </property>
 <property> velocities/q-aero-deg_sec </property>-->
 <!--<property> attitude/phi-rad </property>
 <property> position/h-sl-ft </property>
 <property> velocities/vc-kts </property>
 <property> fcs/throttle-cmd-norm </property>
 <property> fcs/elevator-cmd-norm </property>
 <property> fcs/pitch-trim-cmd-norm </property>
 <property> propulsion/total-fuel-lbs </property>
 <property> flight-path/gamma-rad </property>
 <property> accelerations/n-pilot-z-norm </property>
 <rates> ON </rates>
 <velocities> ON </velocities>
 <forces> ON </forces>
 <moments> ON </moments>
 <position> ON </position>
 <fcs> ON </fcs>
 <propulsion> OFF </propulsion>
 <aerosurfaces> ON </aerosurfaces>
 <fcs> ON </fcs>
 <ground_reactions> ON </ground_reactions>-->
<!--</output>-->

</fdm_config>