<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F-15C Eagle" version="2.0" release="BETA"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author> Fabrice Kauffmann </author>
        <filecreationdate> 2007-01-27 </filecreationdate>
        <version> $Revision$ </version>
        <description> Models a F-15C Eagle based on the F-16A Block-32 from Erik Hofman </description>
        <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="" title="wind tunnel data" date="12/1979"/>
        <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> -189.5 </x>
            <y> 0 </y>
            <z> 3.9 </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> 0 </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> -5.1 </z>
        </location>
        <pointmass name="Pilot">
            <weight unit="LBS"> 230 </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> -73 </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"> 15000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
            <max_steer unit="DEG"> 80 </max_steer>
            <brake_group> NOSE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MLG">
            <location unit="IN">
                <x> -108.6 </x>
                <y> -48 </y>
                <z> -70 </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"> 22704 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 10000 </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> -108.6 </x>
                <y> 48 </y>
                <z> -70 </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"> 22704 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 10000 </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> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_WT">
            <location unit="IN">
                <x> -121.3 </x>
                <y> 189 </y>
                <z> 0 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="TOP_VS">
            <location unit="IN">
                <x> -27.2 </x>
                <y> 0 </y>
                <z> 123.2 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="LEFT_VFT">
            <location unit="IN">
                <x> -97.6 </x>
                <y> -24.8 </y>
                <z> -52 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 200 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_VFT">
            <location unit="IN">
                <x> -97.6 </x>
                <y> 24.8 </y>
                <z> -52 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 200 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 5000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="INTAKE">
            <location unit="IN">
                <x> -322.4 </x>
                <y> 0 </y>
                <z> -36.6 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="RADOME">
            <location unit="IN">
                <x> -486.6 </x>
                <y> 0 </y>
                <z> -8.7 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
        </contact>
    </ground_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>
            <thruster file="direct">
                <location unit="IN">
                    <x> 0 </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>
        <tank type="FUEL">    <!-- Tank number 0 -->
            <location unit="IN">
                <x> -174.4 </x>
                <y> 65.0 </y>
                <z> 5.0 </z>
            </location>
            <capacity unit="LBS"> 3486 </capacity>
            <contents unit="LBS"> 1500 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 -->
            <location unit="IN">
                <x> -174.4 </x>
                <y> -65.0 </y>
                <z> 5.0 </z>
            </location>
            <capacity unit="LBS"> 3486 </capacity>
            <contents unit="LBS"> 1500 </contents>
        </tank>
        <tank type="FUEL">    <!-- External Tank number 0  (station 4) -->
            <location unit="IN">
                <x> -174.4 </x>
                <y> 65.0 </y>
                <z> -15.0 </z>
            </location>
            <capacity unit="LBS"> 2991 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>
        <tank type="FUEL">    <!-- External Tank number 1 (station 6) -->
            <location unit="IN">
                <x> -174.4 </x>
                <y> -65.0 </y>
                <z> -15.0 </z>
            </location>
            <capacity unit="LBS"> 2991 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>
    </propulsion>
    <flight_control name="F-16 FC">

      <!-- Declare some interface properties -->

        <property>fcs/alpha-norm</property>

        <channel name="Pitch">
            <summer name="elevator cmd limiter">
                <input>fcs/elevator-cmd-norm</input>
                <input>fcs/pitch-trim-cmd-norm</input>
                <bias>-0.1</bias>
                <clipto>
                    <min>-1</min>
                    <max>0.44</max>
                </clipto>
            </summer>

            <pure_gain name="g load norm">
                <input>-accelerations/n-pilot-z-norm</input>
                <gain>0.125</gain>
            </pure_gain>

            <pure_gain name="alpha limiter">
                <input>aero/alpha-rad</input>
                <gain>1.0472</gain>
            </pure_gain>

            <summer name="g load error">
                <input>fcs/elevator-cmd-limiter</input>
                <input>fcs/g-load-norm</input>
                <input>fcs/alpha-limiter</input>
            </summer>

            <pure_gain name="g load p">
                <input>fcs/g-load-error</input>
                <gain>0.66</gain>
            </pure_gain>

            <integrator name="g load i">
                <input>fcs/g-load-error</input>
                <c1>0.005</c1>
            </integrator>

            <lead_lag_filter name="g load d">
                <input>fcs/g-load-error</input>
                <c1>-0.000125</c1>
                <c2>0.0</c2>
                <c3>0.0</c3>
                <c4>1</c4>
            </lead_lag_filter>

            <summer name="g load command">
                <input>fcs/g-load-p</input>
                <input>fcs/g-load-i</input>
                <input>fcs/g-load-d</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
                <output>fcs/elevator-pos-norm</output>
            </summer>

            <aerosurface_scale name="Elevator Control">
                <input>fcs/g-load-command</input>
                <range>
                    <min>-0.436</min>
                    <max>0.436</max>
                </range>
                <output>fcs/elevator-pos-rad</output>
            </aerosurface_scale>

        </channel>

        <channel name="Roll">

            <pure_gain name="roll rate norm">
                <input>velocities/p-aero-rad_sec</input>
                <gain>0.31831</gain>
            </pure_gain>

            <summer name="roll trim error">
                <input>fcs/aileron-cmd-norm</input>
                <!-- input>fcs/roll-trim-cmd-norm</input -->
                <input>-fcs/roll-rate-norm</input>
            </summer>

            <pure_gain name="roll rate p">
                <input>fcs/roll-trim-error</input>
                <gain>3</gain>
            </pure_gain>

            <integrator name="roll rate i">
                <input>fcs/roll-trim-error</input>
                <c1>0.05</c1>
            </integrator>

            <lead_lag_filter name="roll rate d">
                <input>fcs/roll-trim-error</input>
                <c1>-0.00125</c1>
                <c2>0.0</c2>
                <c3>0.0</c3>
                <c4>1</c4>
            </lead_lag_filter>

            <summer name="roll rate command">
                <input>fcs/roll-rate-p</input>
                <input>fcs/roll-rate-i</input>
                <input>fcs/roll-rate-d</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
                <output>fcs/left-aileron-pos-norm</output>
            </summer>

            <aerosurface_scale name="Left Aileron Control">
                <input>fcs/roll-rate-command</input>
                <range>
                    <min>-0.375</min>
                    <max>0.375</max>
                </range>
                <output>fcs/left-aileron-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right Aileron Control">
                <input>-fcs/roll-rate-command</input>
                <range>
                    <min>-0.375</min>
                    <max>0.375</max>
                </range>
                <output>fcs/right-aileron-pos-rad</output>
            </aerosurface_scale>

        </channel>

        <channel name="Yaw">

            <pure_gain name="yaw rate norm">
                <input>velocities/r-aero-rad_sec</input>
                <gain>0.31831</gain>
            </pure_gain>

            <summer name="yaw trim error">
                <input>fcs/rudder-cmd-norm</input>
                <!-- input>fcs/yaw-trim-cmd-norm</input -->
                <input>fcs/yaw-rate-norm</input>
            </summer>

            <pure_gain name="yaw rate p">
                <input>fcs/yaw-trim-error</input>
                <gain>3</gain>
            </pure_gain>

            <integrator name="yaw rate i">
                <input>fcs/yaw-trim-error</input>
                <c1>0.05</c1>
            </integrator>

            <lead_lag_filter name="yaw rate d">
                <input>fcs/yaw-trim-error</input>
                <c1>-0.00125</c1>
                <c2>0.0</c2>
                <c3>0.0</c3>
                <c4>1</c4>
            </lead_lag_filter>

            <summer name="yaw command">
                <input>fcs/yaw-rate-p</input>
                <input>fcs/yaw-rate-i</input>
                <input>fcs/yaw-rate-d</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
                <output>fcs/rudder-pos-norm</output>
            </summer>

            <aerosurface_scale name="Rudder Control">
                <input>fcs/yaw-command</input>
                <range>
                    <min>-0.524</min>
                    <max>0.524</max>
                </range>
                <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>

        </channel>

        <channel name="Leading Edge Flap">

            <pure_gain name="Alpha Norm Gain">
                <input>aero/alpha-rad</input>
                <gain>1.90986</gain>
                <output>fcs/alpha-norm</output>
            </pure_gain>

            <kinematic name="LEF Pos Deg">
                <input>fcs/alpha-norm</input>
                <traverse>
                    <setting>
                        <position>-2</position>
                        <time>0.5</time>
                    </setting>
                    <setting>
                        <position>15</position>
                        <time>1</time>
                    </setting>
                    <setting>
                        <position>25</position>
                        <time>2</time>
                    </setting>
                </traverse>
            </kinematic>

            <!-- ===============================================================
                 Component for Leading edge flap position, NORMALIZED
                 Input: fcs/lef-pos-deg (above)
                 Output: Component (output) value is normalized leading edge
                         flap position, mapping the LEF domain of
                         -2 to +25 degrees into a range of 0 to 1.
            -->
            <aerosurface_scale name="LEF Pos Norm">
              <input>fcs/lef-pos-deg</input>
              <domain>
                <min>-2</min>  <!-- LEF actual minimum position -->
                <max>25</max>  <!-- LEF actual maximum position -->
              </domain>
              <range>
                <min>0</min>  <!-- LEF normalized minimum position -->
                <max>1</max>  <!-- LEF normalized maximum position -->
              </range>
            </aerosurface_scale>

        </channel>

        <channel name="Throttle">

            <pure_gain name="Throttle1">
                <input>fcs/throttle-cmd-norm</input>
                <gain>2</gain>
                <output>fcs/throttle-pos-norm</output>
            </pure_gain>

        </channel>

        <channel name="Flaps">

            <switch name="Flap Command">
                <default value="0"/>
                <test logic="OR" value="1">
                    velocities/vc-kts lt 250
                    gear/gear-cmd-norm == 1
                </test>
            </switch>

            <kinematic name="Flaps Control">
                <input>fcs/flap-command</input>
                <traverse>
                    <setting>
                        <position>-2</position>
                        <time>0.5</time>
                    </setting>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>20</position>
                        <time>3</time>
                    </setting>
                </traverse>
                <output>fcs/flap-pos-deg</output>
            </kinematic>

            <aerosurface_scale name="Flap Position Normalizer">
              <input>fcs/flaps-control</input>
              <domain>
                <min>-2</min>  <!-- Flaps actual minimum position -->
                <max>20</max>  <!-- Flaps actual maximum position -->
              </domain>
              <range>
                <min>0</min>  <!-- Flaps normalized minimum position -->
                <max>1</max>  <!-- Flaps normalized maximum position -->
              </range>
              <output>fcs/flap-pos-norm</output>
            </aerosurface_scale>

        </channel>

        <channel name="Speedbrake">

            <kinematic name="Speedbrake Control">
                <input>fcs/speedbrake-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>1</time>
                    </setting>
                </traverse>
                <output>fcs/speedbrake-pos-norm</output>
            </kinematic>

        </channel>

        <channel name="Landing Gear">

            <kinematic name="Gear Control">
                <input>gear/gear-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>5</time>
                    </setting>
                </traverse>
                <output>gear/gear-pos-norm</output>
            </kinematic>

            <scheduled_gain name="Scheduled Steer Pos Deg">
                <input>fcs/steer-cmd-norm</input>
                <table>
                    <independentVar>velocities/vg-fps</independentVar>
                    <tableData>
                        10.0        80.0
                        50.0        15.0
                        150.0       2.0
                    </tableData>
                </table>
                <output>fcs/steer-pos-deg</output>
            </scheduled_gain>

        </channel>

    </flight_control>

    <aerodynamics>

        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000  1.2290
                          0.1000  1.1240
                          0.1500  1.1160
                          0.2000  1.1240
                          0.3000  1.1050
                          0.4000  1.0410
                          0.5000  1.0340
                          0.6000  1.0190
                          0.7000  1.0080
                          0.8000  1.0030
                          0.9000  1.0010
                          1.0000  1.0000
                          1.1000  1.0000
                      </tableData>
                  </table>
            </product>
        </function>
        <axis name="DRAG">
            <function name="aero/coefficient/CDDh">
                <description>Drag_due_to_horizontal_tail_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table name="CDdHT">
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
                          <tableData>
                                      -0.4360  -0.2180  0.0000  0.2180  0.4360
                              -0.1750  0.2170   0.1740  0.1560  0.1810  0.2300
                              -0.0870  0.0940   0.0550  0.0410  0.0620  0.1010
                               0.0000  0.0810   0.0400  0.0210  0.0390  0.0760
                               0.0870  0.1060   0.0610  0.0400  0.0570  0.1010
                               0.1750  0.1660   0.1190  0.0960  0.1140  0.1580
                               0.2620  0.2520   0.2030  0.1820  0.2020  0.2400
                               0.3490  0.4040   0.3620  0.3470  0.3710  0.4160
                               0.4360  0.6280   0.5880  0.5770  0.6010  0.6370
                               0.5240  0.8750   0.8400  0.8260  0.8520  0.8800
                               0.6110  1.1270   1.0950  1.0840  1.1020  1.1250
                               0.6980  1.3650   1.3340  1.3260  1.3380  1.3560
                               0.7850  1.5170   1.4870  1.4780  1.4820  1.4890
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDmach">
                <description>Drag_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000  0.0000
                              0.8100  0.0000
                              1.1000  0.0230
                              1.8000  0.0150
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDDlef">
                <description>Drag_due_to_leading_edge_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/lef-pos-norm</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  0.0030
                              -0.0870  0.0010
                               0.0000  0.0000
                               0.0870  0.0010
                               0.1750  0.0020
                               0.2620  0.0040
                               0.3490  0.0070
                               0.4360  0.0110
                               0.5240  0.0150
                               0.6110  0.0190
                               0.6980  0.0230
                               0.7850  0.0240
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDDflaps">
                <description>Drag_due_to_trailing_edge_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <value>0.0800</value>
                </product>
            </function>
            <function name="aero/coefficient/CDgear">
                <description>Drag_due_to_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/gear-pos-norm</property>
                    <value>0.0270</value>
                </product>
            </function>
            <function name="aero/coefficient/CDDsb">
                <description>Drag_due_to_speedbrake_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/mag-speedbrake-pos-rad</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.0570
                              -0.0870  -0.0240
                               0.0000  0.0100
                               0.0870  0.0590
                               0.1750  0.1300
                               0.2620  0.2290
                               0.3490  0.2430
                               0.4360  0.2120
                               0.5240  0.1500
                               0.6110  0.1100
                               0.6980  0.1430
                               0.7850  0.1250
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDq">
                <description>Drag_due_to_pitch_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <property>aero/ci2vel</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -1.2650
                              -0.0870  -2.1390
                              0.0000  -0.3080
                              0.0870  1.4020
                              0.1750  3.3690
                              0.2620  5.1350
                              0.3490  6.8800
                              0.4360  10.0600
                              0.5240  13.2010
                              0.6110  15.8720
                              0.6980  23.2170
                              0.7850  24.1050
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDq_Dlef">
                <description>Drag_due_to_pitch_rate_and_leading_edge_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <property>aero/ci2vel</property>
                    <property>fcs/lef-pos-norm</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  0.0670
                              -0.0870  0.0340
                              0.0000  0.0280
                              0.0870  0.0290
                              0.1750  0.0330
                              0.2620  0.0590
                              0.3490  0.0610
                              0.4360  0.0270
                              0.5240  0.0360
                              0.6110  0.0470
                              0.6980  0.0290
                              0.7850  0.0150
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="SIDE">
            <function name="aero/coefficient/CYb">
                <description>Side_force_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/beta-rad</property>
                    <value>-1.1460</value>
                </product>
            </function>
            <function name="aero/coefficient/CYb_M">
                <description>Change_in_Side_force_due_to_beta_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/beta-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.4000  0.0000
                              1.2000  0.0573
                              1.6000  -0.1719
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYDa">
                <description>Side_force_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>-0.0226</value>
                </product>
            </function>
            <function name="aero/coefficient/CYdr">
                <description>Side_force_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.0860</value>
                </product>
            </function>
            <function name="aero/coefficient/CYp">
                <description>Side_force_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.1080
                              -0.0870  -0.1080
                              0.0000  -0.1880
                              0.0870  0.1100
                              0.1750  0.2580
                              0.2620  0.2260
                              0.3490  0.3440
                              0.4360  0.3620
                              0.5240  0.6110
                              0.6110  0.5290
                              0.6980  0.2980
                              0.7850  -0.2270
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CYr">
                <description>Side_force_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  0.8820
                              -0.0870  0.8520
                              0.0000  0.8760
                              0.0870  0.9580
                              0.1750  0.9620
                              0.2620  0.9740
                              0.3490  0.8190
                              0.4360  0.4830
                              0.5240  0.5900
                              0.6110  1.2100
                              0.6980  -0.4930
                              0.7850  -1.0400
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="LIFT">
            <function name="aero/coefficient/CLDh">
                <description>Lift_due_to_horizontal_tail_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
                          <tableData>
                                -0.4360  -0.2180  0.0000  0.2180  0.4360
                              -0.1750  -0.6590  -0.7090  -0.7540  -0.7920  -0.8250
                              -0.0870  -0.1510  -0.1960  -0.2380  -0.2780  -0.3160
                              0.0000  0.1830  0.1410  0.1000  0.0590  0.0170
                              0.0870  0.4910  0.4540  0.4140  0.3710  0.3260
                              0.1750  0.7970  0.7630  0.7250  0.6800  0.6300
                              0.2620  1.1080  1.0790  1.0410  0.9930  0.9400
                              0.3490  1.3950  1.3660  1.3270  1.2740  1.2140
                              0.4360  1.6150  1.5870  1.5470  1.4900  1.4270
                              0.5240  1.8040  1.7770  1.7370  1.6740  1.6100
                              0.6110  1.9000  1.8720  1.8290  1.7660  1.6990
                              0.6980  1.8980  1.8690  1.8220  1.7570  1.6890
                              0.7850  1.7530  1.7240  1.6740  1.6120  1.5460
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLDlef">
                <description>Lift_due_to_leading_edge_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/lef-pos-norm</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.0120
                              -0.0870  -0.0040
                              0.0000  0.0020
                              0.0870  0.0070
                              0.1750  0.0120
                              0.2620  0.0180
                              0.3490  0.0220
                              0.4360  0.0250
                              0.5240  0.0260
                              0.6110  0.0280
                              0.6980  0.0280
                              0.7850  0.0250
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLDflaps">
                <description>Delta_Lift_due_to_trailing_edge_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <property>aero/function/kCLge</property>
                    <value>0.3500</value>
                </product>
            </function>
            <function name="aero/coefficient/CLDsb">
                <description>Lift_due_to_speedbrake_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/mag-speedbrake-pos-rad</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  0.3820
                              -0.0870  0.3850
                              0.0000  0.3860
                              0.0870  0.2640
                              0.1750  0.2840
                              0.2620  0.3790
                              0.3490  0.1340
                              0.4360  0.0080
                              0.5240  -0.1370
                              0.6110  -0.1920
                              0.6980  -0.1220
                              0.7850  -0.1110
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLq">
                <description>Lift_due_to_pitch_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <property>aero/ci2vel</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  8.7127
                              -0.0870  25.7114
                              0.0000  28.9000
                              0.0870  31.3973
                              0.1750  31.0872
                              0.2620  30.4071
                              0.3490  26.9735
                              0.4360  26.4242
                              0.5240  25.8647
                              0.6110  25.2654
                              0.6980  30.5158
                              0.7850  25.8165
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CLq_Dsb">
                <description>Lift_due_to_speedbrake_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>velocities/q-aero-rad_sec</property>
                    <property>aero/ci2vel</property>
                    <property>fcs/mag-speedbrake-pos-rad</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.2560
                              -0.0870  -0.0620
                              0.0000  -0.0100
                              0.0870  0.0200
                              0.1750  -0.0110
                              0.2620  0.0530
                              0.3490  0.0630
                              0.4360  -0.0090
                              0.5240  0.0340
                              0.6110  0.0420
                              0.6980  0.0050
                              0.7850  0.0010
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="ROLL">
            <function name="aero/coefficient/Clb">
                <description>Roll_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/beta-rad</independentVar>
                          <tableData>
                                -0.5240  -0.4360  -0.3490  -0.2620  -0.1750  -0.0870  0.0000  0.0870  0.1750  0.2620  0.3490  0.4360  0.5240
                              -0.1750  -0.0090  -0.0070  -0.0000  0.0010  0.0030  0.0010  0.0000  -0.0010  -0.0030  -0.0010  0.0000  0.0070  0.0090
                              -0.0870  0.0110  0.0100  0.0100  0.0100  0.0090  0.0040  0.0000  -0.0040  -0.0090  -0.0100  -0.0100  -0.0100  -0.0110
                              0.0000  0.0230  0.0230  0.0220  0.0200  0.0170  0.0080  0.0000  -0.0080  -0.0170  -0.0200  -0.0220  -0.0230  -0.0230
                              0.0870  0.0370  0.0340  0.0340  0.0300  0.0240  0.0120  0.0000  -0.0120  -0.0240  -0.0300  -0.0340  -0.0340  -0.0370
                              0.1750  0.0500  0.0490  0.0470  0.0390  0.0300  0.0160  0.0000  -0.0160  -0.0300  -0.0390  -0.0470  -0.0490  -0.0500
                              0.2620  0.0680  0.0630  0.0600  0.0540  0.0410  0.0220  0.0000  -0.0220  -0.0410  -0.0540  -0.0600  -0.0630  -0.0680
                              0.3490  0.0890  0.0810  0.0690  0.0570  0.0450  0.0220  0.0000  -0.0220  -0.0450  -0.0570  -0.0690  -0.0810  -0.0890
                              0.4360  0.0880  0.0790  0.0670  0.0540  0.0400  0.0210  0.0000  -0.0210  -0.0400  -0.0540  -0.0670  -0.0790  -0.0880
                              0.5240  0.0910  0.0600  0.0330  0.0230  0.0160  0.0150  0.0000  -0.0150  -0.0160  -0.0230  -0.0330  -0.0600  -0.0910
                              0.6110  0.0760  0.0580  0.0360  0.0060  0.0020  0.0080  0.0000  -0.0080  -0.0020  -0.0060  -0.0360  -0.0580  -0.0760
                              0.6980  0.0770  0.0620  0.0350  0.0140  0.0100  0.0130  0.0000  -0.0130  -0.0100  -0.0140  -0.0350  -0.0620  -0.0770
                              0.7850  0.0760  0.0590  0.0350  0.0270  0.0190  0.0150  0.0000  -0.0150  -0.0190  -0.0270  -0.0350  -0.0590  -0.0760
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clb_M">
                <description>Change_in_Roll_moment_due_to_beta_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              0.8000  0.1891
                              1.0000  0.1776
                              1.2000  0.1375
                              1.4000  0.1203
                              1.6000  0.0859
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.3600
                              -0.0870  -0.3590
                              0.0000  -0.4430
                              0.0870  -0.4200
                              0.1750  -0.3830
                              0.2620  -0.3750
                              0.3490  -0.3290
                              0.4360  -0.2940
                              0.5240  -0.2300
                              0.6110  -0.2100
                              0.6980  -0.1200
                              0.7850  -0.1000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clr">
                <description>Roll_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.1260
                              -0.0870  -0.0260
                              0.0000  0.0630
                              0.0870  0.1130
                              0.1750  0.2080
                              0.2620  0.2300
                              0.3490  0.3190
                              0.4360  0.4370
                              0.5240  0.6800
                              0.6110  0.1000
                              0.6980  0.4470
                              0.7850  -0.3300
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clda">
                <description>Roll_moment_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/beta-rad</independentVar>
                          <tableData>
                                -0.5240  -0.3490  -0.1750  0.0000  0.1750  0.3490  0.5240
                              -0.1750  0.0410  0.0410  0.0420  0.0400  0.0430  0.0440  0.0430
                              -0.0870  0.0520  0.0530  0.0530  0.0520  0.0490  0.0480  0.0490
                              0.0000  0.0530  0.0530  0.0520  0.0510  0.0480  0.0480  0.0470
                              0.0870  0.0560  0.0530  0.0510  0.0520  0.0490  0.0470  0.0450
                              0.1750  0.0500  0.0500  0.0490  0.0480  0.0430  0.0420  0.0420
                              0.2620  0.0560  0.0510  0.0490  0.0480  0.0420  0.0410  0.0370
                              0.3490  0.0820  0.0660  0.0430  0.0420  0.0420  0.0200  0.0030
                              0.4360  0.0590  0.0430  0.0350  0.0370  0.0360  0.0280  0.0130
                              0.5240  0.0420  0.0380  0.0260  0.0310  0.0250  0.0130  0.0100
                              0.6110  0.0380  0.0270  0.0160  0.0260  0.0210  0.0140  0.0030
                              0.6980  0.0270  0.0230  0.0180  0.0170  0.0160  0.0110  0.0070
                              0.7850  0.0170  0.0160  0.0140  0.0120  0.0110  -0.0100  0.0080
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Clda_M">
                <description>Change_in_Roll_moment_due_to_aileron_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/alpha-rad</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              1.2000  -0.0630
                              1.6000  -0.0630
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cldr_M">
                <description>Change_in_Roll_moment_due_to_rudder_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/alpha-rad</property>
                    <property>fcs/rudder-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              1.6000  -0.0201
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cldr">
                <description>Roll_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/beta-rad</independentVar>
                          <tableData>
                                -0.5240  -0.3490  -0.1750  0.0000  0.1750  0.3490  0.5240
                              -0.1750  0.0050  0.0070  0.0130  0.0180  0.0150  0.0210  0.0230
                              -0.0870  0.0170  0.0160  0.0130  0.0150  0.0140  0.0110  0.0100
                              0.0000  0.0140  0.0140  0.0110  0.0150  0.0130  0.0100  0.0110
                              0.0870  0.0100  0.0140  0.0120  0.0140  0.0130  0.0110  0.0110
                              0.1750  -0.0050  0.0130  0.0110  0.0140  0.0120  0.0100  0.0110
                              0.2620  0.0090  0.0090  0.0090  0.0140  0.0110  0.0090  0.0100
                              0.3490  0.0190  0.0120  0.0080  0.0140  0.0110  0.0080  0.0080
                              0.4360  0.0050  0.0050  0.0050  0.0150  0.0100  0.0100  0.0100
                              0.5240  0.0000  0.0000  0.0000  0.0130  0.0080  0.0060  0.0060
                              0.6110  -0.0050  0.0040  0.0050  0.0110  0.0080  0.0050  0.0140
                              0.6980  -0.0110  0.0090  0.0030  0.0060  0.0070  0.0000  0.0200
                              0.7850  0.0080  0.0070  0.0050  0.0010  0.0030  0.0010  0.0000
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/CmDh">
                <description>Pitch_moment_due_to_horizontal_tail_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
                          <tableData>
                                -0.4360  -0.2180  0.0000  0.2180  0.4360
                              -0.1750  0.2050  0.0810  -0.0460  -0.1740  -0.2590
                              -0.0870  0.1680  0.0770  -0.0200  -0.1450  -0.2020
                              0.0000  0.1860  0.1070  -0.0090  -0.1210  -0.1840
                              0.0870  0.1960  0.1100  -0.0050  -0.1270  -0.1930
                              0.1750  0.2130  0.1100  -0.0060  -0.1290  -0.1990
                              0.2620  0.2510  0.1410  0.0100  -0.1020  -0.1500
                              0.3490  0.2450  0.1270  0.0060  -0.0970  -0.1600
                              0.4360  0.2380  0.1190  -0.0010  -0.1130  -0.1670
                              0.5240  0.2520  0.1330  0.0140  -0.0870  -0.1040
                              0.6110  0.2310  0.1080  0.0000  -0.0840  -0.0760
                              0.6980  0.1980  0.0810  -0.0130  -0.0690  -0.0410
                              0.7850  0.1920  0.0930  0.0320  -0.0060  -0.0050
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cma_M">
                <description>Change_in_Pitch_moment_due_to_alpha_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/alpha-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              0.8000  0.0974
                              0.9000  -0.3323
                              1.0000  -0.9626
                              1.1000  -0.8480
                              1.2000  -0.7907
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cmq">
                <description>Pitch_moment_due_to_pitch_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>velocities/q-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -7.2100
                              -0.0870  -5.4000
                              0.0000  -5.2300
                              0.0870  -5.2600
                              0.1750  -6.1100
                              0.2620  -6.6400
                              0.3490  -5.6900
                              0.4360  -6.0000
                              0.5240  -6.2000
                              0.6110  -6.4000
                              0.6980  -6.6000
                              0.7850  -6.0000
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>

        <axis name="YAW">
            <function name="aero/coefficient/Cnb">
                <description>Yaw_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/beta-rad</independentVar>
                          <tableData>
                                -0.5240  -0.4360  -0.3490  -0.2620  -0.1750  -0.0870  0.0000  0.0870  0.1750  0.2620  0.3490  0.4360  0.5240
                              -0.1750  -0.0790  -0.0740  -0.0640  -0.0560  -0.0380  -0.0180  0.0000  0.0180  0.0380  0.0560  0.0640  0.0740  0.0790
                              -0.0870  -0.0900  -0.0860  -0.0770  -0.0570  -0.0420  -0.0190  0.0000  0.0190  0.0420  0.0570  0.0770  0.0860  0.0900
                              0.0000  -0.1060  -0.0930  -0.0760  -0.0590  -0.0420  -0.0180  0.0000  0.0180  0.0420  0.0590  0.0760  0.0930  0.1060
                              0.0870  -0.1060  -0.0890  -0.0740  -0.0580  -0.0420  -0.0190  0.0000  0.0190  0.0420  0.0580  0.0740  0.0890  0.1060
                              0.1750  -0.0960  -0.0800  -0.0730  -0.0580  -0.0430  -0.0190  0.0000  0.0190  0.0430  0.0580  0.0730  0.0800  0.0960
                              0.2620  -0.0800  -0.0620  -0.0570  -0.0530  -0.0390  -0.0180  0.0000  0.0180  0.0390  0.0530  0.0570  0.0620  0.0800
                              0.3490  -0.0680  -0.0490  -0.0290  -0.0320  -0.0300  -0.0130  0.0000  0.0130  0.0300  0.0320  0.0290  0.0490  0.0680
                              0.4360  -0.0300  -0.0220  -0.0070  -0.0120  -0.0170  -0.0070  0.0000  0.0070  0.0170  0.0120  0.0070  0.0220  0.0300
                              0.5240  -0.0640  -0.0280  -0.0120  -0.0020  -0.0040  -0.0040  0.0000  0.0040  0.0040  0.0020  0.0120  0.0280  0.0640
                              0.6110  -0.0150  0.0120  0.0340  0.0460  0.0350  0.0140  0.0000  -0.0140  -0.0350  -0.0460  -0.0340  -0.0120  0.0150
                              0.6980  -0.0110  0.0020  0.0650  0.0710  0.0470  0.0170  0.0000  -0.0170  -0.0470  -0.0710  -0.0650  -0.0020  0.0110
                              0.7850  0.0010  0.0130  0.0410  0.0730  0.0570  0.0330  0.0000  -0.0330  -0.0570  -0.0730  -0.0410  -0.0130  -0.0010
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnb_M">
                <description>Change_in_Yaw_moment_due_to_beta_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              0.7000  -0.0688
                              0.8000  -0.0172
                              0.9000  0.0229
                              1.0000  0.0000
                              1.2000  -0.0688
                              1.4000  0.0057
                              1.6000  0.0688
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnp">
                <description>Yaw_moment_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.0610
                              -0.0870  -0.0520
                              0.0000  -0.0520
                              0.0870  0.0120
                              0.1750  0.0130
                              0.2620  0.0240
                              0.3490  -0.0500
                              0.4360  -0.1500
                              0.5240  -0.1300
                              0.6110  -0.1580
                              0.6980  -0.2400
                              0.7850  -0.1500
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnr">
                <description>Yaw_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.1750  -0.3800
                              -0.0870  -0.3630
                              0.0000  -0.3780
                              0.0870  -0.3860
                              0.1750  -0.3700
                              0.2620  -0.4530
                              0.3490  -0.5500
                              0.4360  -0.5820
                              0.5240  -0.5950
                              0.6110  -0.6370
                              0.6980  -1.0200
                              0.7850  -0.8400
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnda_M">
                <description>Change_in_Yaw_moment_due_to_aileron_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              0.8000  0.0149
                              1.0000  -0.0011
                              1.2000  0.0097
                              1.4000  0.0126
                              1.6000  -0.0040
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <description>Yaw_moment_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/beta-rad</independentVar>
                          <tableData>
                                -0.5240  -0.3490  -0.1750  0.0000  0.1750  0.3490  0.5240
                              -0.1750  0.0010  0.0020  0.0060  0.0110  0.0150  0.0240  -0.0220
                              -0.0870  0.0270  0.0140  0.0080  0.0110  0.0150  0.0100  -0.0020
                              0.0000  0.0170  0.0160  0.0060  0.0100  0.0140  0.0040  0.0030
                              0.0870  0.0130  0.0160  0.0060  0.0090  0.0120  0.0020  0.0050
                              0.1750  0.0120  0.0140  0.0050  0.0080  0.0110  0.0010  0.0030
                              0.2620  0.0160  0.0190  0.0080  0.0060  0.0080  -0.0030  0.0010
                              0.3490  -0.0010  0.0210  0.0050  -0.0000  0.0020  -0.0140  0.0090
                              0.4360  -0.0170  -0.0020  -0.0070  -0.0040  -0.0020  -0.0060  0.0090
                              0.5240  -0.0110  -0.0120  -0.0040  -0.0070  -0.0060  0.0010  0.0010
                              0.6110  -0.0170  -0.0160  -0.0070  -0.0100  -0.0120  -0.0040  -0.0030
                              0.6980  -0.0080  -0.0150  -0.0060  -0.0040  -0.0110  -0.0040  0.0020
                              0.7850  -0.0160  -0.0110  -0.0060  -0.0100  -0.0110  -0.0060  -0.0010
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cndr">
                <description>Yaw_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">aero/beta-rad</independentVar>
                          <tableData>
                                -0.5240  -0.3490  -0.1750  0.0000  0.1750  0.3490  0.5240
                              -0.1750  -0.0180  -0.0280  -0.0370  -0.0480  -0.0430  -0.0520  -0.0620
                              -0.0870  -0.0520  -0.0510  -0.0410  -0.0450  -0.0440  -0.0340  -0.0340
                              0.0000  -0.0520  -0.0430  -0.0380  -0.0450  -0.0410  -0.0360  -0.0270
                              0.0870  -0.0520  -0.0460  -0.0400  -0.0450  -0.0410  -0.0360  -0.0280
                              0.1750  -0.0540  -0.0450  -0.0400  -0.0440  -0.0400  -0.0350  -0.0270
                              0.2620  -0.0490  -0.0490  -0.0380  -0.0450  -0.0380  -0.0280  -0.0270
                              0.3490  -0.0590  -0.0570  -0.0370  -0.0470  -0.0340  -0.0240  -0.0230
                              0.4360  -0.0510  -0.0520  -0.0300  -0.0480  -0.0350  -0.0230  -0.0230
                              0.5240  -0.0300  -0.0300  -0.0270  -0.0490  -0.0350  -0.0200  -0.0190
                              0.6110  -0.0370  -0.0330  -0.0240  -0.0450  -0.0290  -0.0160  -0.0090
                              0.6980  -0.0260  -0.0300  -0.0190  -0.0330  -0.0220  -0.0100  -0.0250
                              0.7850  -0.0130  -0.0080  -0.0130  -0.0160  -0.0090  -0.0140  -0.0100
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cndr_M">
                <description>Change_in_Yaw_moment_due_to_rudder_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/alpha-rad</property>
                    <property>fcs/rudder-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.6000  0.0000
                              1.2000  0.0401
                              1.6000  0.0716
                          </tableData>
                      </table>
                </product>
            </function>
        </axis>
    </aerodynamics>
</fdm_config>
