<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="C150L" version="2.0" release="BETA"
 xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
 xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author> hjohnsen, rjensen </author>
        <filecreationdate> 2005/05/15 </filecreationdate>
        <version> Version </version>
        <description> Models a C150L </description>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 160 </wingarea>
        <wingspan unit="FT"> 33.0 </wingspan>
        <chord unit="FT"> 4.86 </chord>
        <htailarea unit="FT2"> 17.0 </htailarea>
        <htailarm unit="FT"> 17.4 </htailarm>
        <vtailarea unit="FT2"> 9.35 </vtailarea>
        <vtailarm unit="FT"> 17.8 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 77.4 </x>
            <y> 0 </y>
            <z> 27.0 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2"> 551 </ixx>
        <iyy unit="SLUG*FT2"> 759 </iyy>
        <izz unit="SLUG*FT2"> 1069 </izz>
        <ixy unit="SLUG*FT2"> 0 </ixy>
        <ixz unit="SLUG*FT2"> 0 </ixz>
        <iyz unit="SLUG*FT2"> 0 </iyz>
        <emptywt unit="LBS"> 1111 </emptywt>
        <location name="CG" unit="IN">
            <x> 77.4 </x>
            <y> 0 </y>
            <z> -15.75 </z>
        </location>
        <pointmass name="name">
            <weight unit="LBS"> 150 </weight>
            <location name="POINTMASS" unit="M">
                <x> 2.20 </x>
                <y> 0 </y>
                <z> -0.30 </z>
            </location>
        </pointmass>
        <pointmass name="name">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="M">
                <x> 2.20 </x>
                <y> 0 </y>
                <z> -0.30 </z>
            </location>
        </pointmass>
        <pointmass name="name">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="M">
                <x> 3.0 </x>
                <y> 0 </y>
                <z> -0.30 </z>
            </location>
        </pointmass>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="NOSE_LG">
            <location unit="IN">
                <x> 31.7 </x>
                <y> 0 </y>
                <z> -48.43 </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"> 1500 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 500 </damping_coeff>
            <max_steer unit="DEG"> 7 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="LEFT_MLG">
            <location unit="M">
                <x> 2.33099 </x>
                <y> -1.14064 </y>
                <z> -1.18377 </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"> 4000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1300 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MLG">
            <location unit="M">
                <x> 2.33099 </x>
                <y> 1.14064 </y>
                <z> -1.18377 </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"> 4000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 1300 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>0</retractable>
        </contact>
        
        <contact type="STRUCTURE" name="NOSE">
            <location unit="M">
                <x> 0.0 </x>
                <y> 0.0 </y>
                <z> 0.0619576 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.25 </dynamic_friction>
            <spring_coeff unit="LBS/FT">       2000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">   1000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="NOSE_BOTTOM">
            <location unit="M">
                <x> 0.48664 </x>
                <y> 0.0 </y>
                <z> -0.420692 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.25 </dynamic_friction>
            <spring_coeff unit="LBS/FT">       2000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">   1000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="RUDDER_TOP">
            <location unit="M">
                <x> 6.63313 </x>
                <y> 0.0 </y>
                <z> 1.19687 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.25 </dynamic_friction>
            <spring_coeff unit="LBS/FT">       2000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">   1000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="TAIL_SKID">
            <location unit="M">
                <x> 6.28476 </x>
                <y> 0 </y>
                <z> -0.334408 </z>
            </location>
            <static_friction> 0.5 </static_friction>
            <dynamic_friction> 0.25 </dynamic_friction>
            <spring_coeff unit="LBS/FT">       2000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">   1000 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="LEFT_TIP">
            <location unit="M">
                <x> 2.21429 </x>
                <y> -4.96408 </y>
                <z> 0.65408 </z>
            </location>
            <static_friction> 0.75 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <spring_coeff unit="LBS/FT">       1830.15 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">   366.03 </damping_coeff>
        </contact>
        <contact type="STRUCTURE" name="RIGHT_TIP">
            <location unit="M">
                <x> 2.21429 </x>
                <y> 4.96408 </y>
                <z> 0.65408 </z>
            </location>
            <static_friction> 0.75 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <spring_coeff unit="LBS/FT">       1830.15 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC">   366.03 </damping_coeff>
        </contact>

    </ground_reactions>
    <propulsion>
        <engine file="eng_O-200">
            <location unit="IN">
                <x> 12 </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>
            <thruster file="prop_mccauley_6948">
                <location unit="IN">
                    <x> -3.3 </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> 77.4 </x>
                <y> 40 </y>
                <z> 27.0 </z>
            </location>
            <capacity unit="LBS"> 68 </capacity>
            <contents unit="LBS"> 0 </contents>
            <density unit="LBS/GAL"> 6.02 </density>            
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 --> 
            <location unit="IN">
                <x> 77.4 </x>
                <y> -40 </y>
                <z> 27.0 </z>
            </location>
            <capacity unit="LBS"> 68 </capacity>
            <contents unit="LBS"> 0 </contents>
            <density unit="LBS/GAL"> 6.02 </density>            
        </tank>
        <tank type="FUEL">    <!-- Tank number 2 --> 
            <location unit="M">
                <x> 3.0 </x>
                <y> 0 </y>
                <z> -0.30 </z>
            </location>
            <capacity unit="LBS"> 198 </capacity>
            <contents unit="LBS"> 0 </contents>
            <density unit="LBS/GAL"> 6.02 </density>            
        </tank>
    </propulsion>
    <flight_control name="FCS: c150">
     <channel name="All">

        <summer name="Pitch Trim Sum">
            <input>fcs/elevator-cmd-norm</input>
            <input>fcs/pitch-trim-cmd-norm</input>
            <clipto>
                <min>-1</min>
                <max>1</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Elevator Control">
            <input>fcs/pitch-trim-sum</input>
            <gain>0.01745</gain>
            <range>
                <min>-26</min>
                <max>17</max>
            </range>
            <output>fcs/elevator-pos-rad</output>
        </aerosurface_scale>
            <aerosurface_scale name="Elevator Position Normalized">
                <input>fcs/elevator-pos-deg</input>
                <domain>
  	            <min>-26</min>
  	            <max>17</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/elevator-pos-norm</output>
            </aerosurface_scale>

        <summer name="Roll Trim Sum">
            <input>fcs/aileron-cmd-norm</input>
            <input>fcs/roll-trim-cmd-norm</input>
            <clipto>
                <min>-1</min>
                <max>1</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Left Aileron Control">
            <input>fcs/roll-trim-sum</input>
            <gain>0.01745</gain>
            <range>
                <min>-20</min>
                <max>14</max>
            </range>
            <output>fcs/left-aileron-pos-rad</output>
        </aerosurface_scale>
            <aerosurface_scale name="Left Aileron Position Normalized">
                <input>fcs/left-aileron-pos-deg</input>
                <domain>
  	            <min>-20</min>
  	            <max>14</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/left-aileron-pos-norm</output>
            </aerosurface_scale>

        <aerosurface_scale name="Right Aileron Control">
            <input>fcs/roll-trim-sum</input>
            <gain>-0.01745</gain>
            <range>
                <min>-20</min>
                <max>14</max>
            </range>
            <output>fcs/right-aileron-pos-rad</output>
        </aerosurface_scale>
            <aerosurface_scale name="Right Aileron Position Normalized">
                <input>fcs/right-aileron-pos-deg</input>
                <domain>
  	            <min>-20</min>
  	            <max>14</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/right-aileron-pos-norm</output>
            </aerosurface_scale>

        <summer name="Rudder Command Sum">
            <input>fcs/rudder-cmd-norm</input>
            <input>fcs/yaw-trim-cmd-norm</input>
            <clipto>
                <min>-1</min>
                <max>1</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Rudder Control">
            <input>fcs/rudder-command-sum</input>
            <gain>0.01745</gain>
            <range>
                <min>-23</min>
                <max>23</max>
            </range>
            <output>fcs/rudder-pos-rad</output>
        </aerosurface_scale>
            <aerosurface_scale name="Rudder Position Normalized">
                <input>fcs/rudder-pos-deg</input>
                <domain>
  	            <min>-23</min>
  	            <max>23</max>
                </domain>
                <range>
                    <min>-1</min>
                    <max>1</max>
                </range>
                <output>fcs/rudder-pos-norm</output>
            </aerosurface_scale>

        <kinematic name="Flaps Control">
            <input>fcs/flap-cmd-norm</input>
            <traverse>
                <setting>
                    <position>0</position>
                    <time>0</time>
                </setting>
                <setting>
                    <position>10</position>
                    <time>1</time>
                </setting>
                <setting>
                    <position>20</position>
                    <time>1</time>
                </setting>
                <setting>
                    <position>30</position>
                    <time>1</time>
                </setting>
                <setting>
                    <position>40</position>
                    <time>1</time>
                </setting>
            </traverse>
            <output>fcs/flap-pos-deg</output>
        </kinematic>
            <aerosurface_scale name="Flap Position Normalizer">
              <input>fcs/flap-pos-deg</input>
              <domain>
                <min>0</min>  <!-- Flaps actual minimum position -->
                <max>40</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>

        <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>
    </flight_control>
    <aerodynamics>

      <alphalimits unit="DEG">
         <min>-5.0</min>
         <max>14.0</max>
      </alphalimits>

      <hysteresis_limits unit="DEG">
         <min> 5.0</min>
         <max>20.0</max>
      </hysteresis_limits>

      <function name="aero/function/ground-effect-factor-lift">
         <description>Change in lift due to ground effect factor</description>
         <product>
            <table>
               <independentVar>aero/h_b-mac-ft</independentVar>
               <tableData>
                  0.0  1.203
                  0.1  1.127
                  0.15 1.090
                  0.2  1.073
                  0.3  1.046
                  0.4  1.055
                  0.5  1.019
                  0.6  1.013
                  0.7  1.008
                  0.8  1.006
                  0.9  1.003
                  1.0  1.002
                  1.1  1.0
               </tableData>
            </table>
         </product>
      </function>

      <function name="aero/function/ground-effect-factor-drag">
         <description>Change in drag due to ground effect</description>
         <product>
            <table>
               <independentVar>aero/h_b-mac-ft</independentVar>
               <tableData>
                  0.0  0.480
                  0.1  0.515
                  0.15 0.629
                  0.2  0.709
                  0.3  0.815
                  0.4  0.882
                  0.5  0.928
                  0.6  0.962
                  0.7  0.988
                  0.8  1.0
                  0.9  1.0
                  1.0  1.0
                  1.1  1.0
               </tableData>
            </table>
         </product>
      </function>

        <axis name="DRAG">
            <function name="aero/coefficient/CD0">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/function/ground-effect-factor-drag</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -1.5700	1.5000	
                       -.2793         .1014    
                       -.1396         .2981E-01
                       -.1047         .2156E-01
                       -.6981E-01     .1687E-01
                       -.3491E-01     .1535E-01
                         .000         .1702E-01
                        .3491E-01     .2225E-01
                        .6981E-01     .3142E-01
                        .1396         .6338E-01
                        .1571         .7447E-01
                        .1745         .8682E-01
                        .2094         .1123    
                        .2443         .1366    
                        .2793         .1595    
                        .3142         .1797    
                        .3316         .1885    
                        .3491         .1886    
                        .3665         .1852    
                        .3840         .1610    
                        .4189         .1039    
                              1.5700	1.5000	
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDi">
                <description>Induced_drag</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/cl-squared</property>
                    <value>0.0100</value>
                </product>
            </function>
            <function name="aero/coefficient/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-deg</property>
                    <value>0.0010</value>
                </product>
            </function>
            <function name="aero/coefficient/CDsb">
                <description>Drag_due_to_speedbrakes</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>0.0280</value>
                </product>
            </function>
            <function name="aero/coefficient/CDbeta">
                <description>Drag_due_to_sideslip</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/beta-rad</independentVar>
                          <tableData>
                              -1.5700	1.2300	
                              -0.2600	0.0500	
                              0.0000	0.0000	
                              0.2600	0.0500	
                              1.5700	1.2300	
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDde">
                <description>Drag_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sh-sqft</property>
                    <abs><property>fcs/elevator-pos-norm</property></abs>
                    <value>0.0300</value>
                </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>-.2927</value>
                </product>
            </function>
        </axis>

        <axis name="LIFT">
            <function name="aero/coefficient/CLalpha">
                <description>Lift_due_to_alpha</description>
                <product>
                    <property>aero/function/ground-effect-factor-lift</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                       -.2793        -1.298    
                       -.1396        -.5118    
                       -.1047        -.3244    
                       -.6981E-01    -.1446    
                       -.3491E-01     .2816E-01
                         .000         .2070    
                        .3491E-01     .3944    
                        .6981E-01     .5894    
                        .1396         1.002    
                        .1571         1.108    
                        .1745         1.216    
                        .2094         1.409    
                        .2443         1.565    
                        .2793         1.691    
                        .3142         1.783    
                        .3316         1.814    
                        .3491         1.791    
                        .3665         1.737    
                        .3840         1.531    
                        .4189         .6785    
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/dCLflap">
                <description>Delta_Lift_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-deg</property>
                    <value>0.01333</value>
                </product>
            </function>
            <function name="aero/coefficient/dCLsb">
                <description>Delta_Lift_due_to_speedbrake</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>0.0000</value>
                </product>
            </function>
            <function name="aero/coefficient/CLde">
                <description>Lift_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
               <table>
                  <independentVar>fcs/elevator-pos-deg</independentVar>
                  <tableData>
      -26.00	   .1787    
      -17.00	   .1664    
      -10.00	   .1138    
       -5.00	   .5690E-01
         .00	  -.1138E-03
        5.00	  -.5690E-01
        9.00	  -.1024    
       13.00	  -.1434    
       17.00	  -.1664    
                  </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>
                    <property>aero/beta-rad</property>
                    <value>-0.0890</value>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_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>
                    <value>-0.4700</value>
                </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>
                    <value>0.0960</value>
                </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>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1700	
                              2.0000	0.0570	
                          </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>
                    <value>0.0140</value>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/Cmalpha">
                <description>Pitch_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/alpha-rad</property>
                    <value>-5.2000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/elevator-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-1.1000	
                              2.0000	-0.2750	
                          </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>
                    <value>-12.4000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmadot">
                <description>Pitch_moment_due_to_alpha_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>aero/alphadot-rad_sec</property>
                    <value>-0.8900</value>
                </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>
                    <property>aero/beta-rad</property>
                    <value>0.0650</value>
                </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>
                    <value>-0.0990</value>
                </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>
                    <value>-0.0660</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <description>Adverse_yaw</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>-0.0100</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
</fdm_config>
