C-130JJSBsim.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="C-130JJSBsim" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Aeromatic v 0.95 </author>
  <filecreationdate>2016-07-11</filecreationdate>
  <version>$Revision: 1.15 $</version>
  <description> Models a C-130JJSBsim. </description>
 </fileheader>

<!--
  File:     C-130JJSBsim.xml
  Inputs:
    name:          C-130JJSBsim
    type:          multi-engine prop transport
    max weight:    155000 lb
    wing span:     132.7 ft
    length:        97.9 ft
    wing area:     1742 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   turboprop
    engine layout: wings
    yaw damper?    yes
  Outputs:
    wing loading:  88.98 lb/sq-ft
    payload:       40068.0 lbs
    CL-alpha:      4.9 per radian
    CL-0:          0.24
    CL-max:        1.4
    CD-0:          0.025
    K:             0.039

-->

 <metrics>
   <wingarea  unit="FT2"> 1742.00 </wingarea>
   <wingspan  unit="FT" >  132.70 </wingspan>
   <wing_incidence>          3.00 </wing_incidence>
   <chord     unit="FT" >   13.13 </chord>
   <htailarea unit="FT2">  278.72 </htailarea>
   <htailarm  unit="FT" >   48.95 </htailarm>
   <vtailarea unit="FT2">  313.56 </vtailarea>
   <vtailarm  unit="FT" >   48.95 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 610.40 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  93.98 </x>
     <y> -24.00 </y>
     <z>  65.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">   1057863 </ixx>
   <iyy unit="SLUG*FT2">    688794 </iyy>
   <izz unit="SLUG*FT2">   1722828 </izz>
   <emptywt unit="LBS" >     75562 </emptywt>
   <location name="CG" unit="IN">
     <x> 600.40 </x>
     <y>   0.00 </y>
     <z> -29.37 </z>
   </location>
   <pointmass name="Payload">
    <description> 40068 LBS + full (39370 LBS) fuel should bring model up to entered max weight</description>
    <weight unit="LBS">  0 </weight>
    <location name="POINTMASS" unit="IN">
      <x> 600.40 </x>
      <y>   0.00 </y>
      <z> -29.37 </z>
    </location>
  </pointmass> 
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 152.72 </x>
     <y>   0.00 </y>
     <z> -41.98 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.05 </rolling_friction>
   <spring_coeff unit="LBS/FT">      46500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 77500.00 </damping_coeff>
   <max_steer unit="DEG"> 30.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
  </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 610.90 </x>
     <y> -175.16 </y>
     <z> -39.98 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      155000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 77500.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
  </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x> 610.90 </x>
     <y> 175.16 </y>
     <z> -39.98 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">      155000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 77500.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
  </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 600.40 </x>
     <y> -66.35 </y>
     <z> -29.37 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      155000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 100000.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 600.40 </x>
     <y>  66.35 </y>
     <z> -29.37 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      155000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 100000.00 </damping_coeff>
  </contact>

 </ground_reactions>

 <propulsion>

   <engine file="AE2100D3">
    <location unit="IN">
      <x> 600.40 </x>
      <y> -265.40 </y>
      <z> -40.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>4</feed>
    <thruster file="R391">
     <location unit="IN">
       <x> 600.40 </x>
       <y> -265.40 </y>
       <z> -40.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="AE2100D3">
    <location unit="IN">
      <x> 610.40 </x>
      <y> -265.40 </y>
      <z> -40.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>4</feed>
    <thruster file="R391">
     <location unit="IN">
       <x> 610.40 </x>
       <y> -265.40 </y>
       <z> -40.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="AE2100D3">
    <location unit="IN">
      <x> 610.40 </x>
      <y> 265.40 </y>
      <z> -40.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>2</feed>
    <feed>4</feed>
    <thruster file="R391">
     <location unit="IN">
       <x> 60.40 </x>
       <y> 265.40 </y>
       <z> -40.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="AE2100D3">
    <location unit="IN">
      <x> 610.40 </x>
      <y> 265.40 </y>
      <z> -40.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>3</feed>
    <feed>4</feed>
    <thruster file="R391">
     <location unit="IN">
       <x> 610.40 </x>
       <y> 265.40 </y>
       <z> -40.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> 600.40 </x>
       <y>   0.00 </y>
       <z> -29.37 </z>
     </location>
     <capacity unit="LBS"> 7874.00 </capacity>
     <contents unit="LBS"> 3937.00 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 600.40 </x>
       <y>   0.00 </y>
       <z> -29.37 </z>
     </location>
     <capacity unit="LBS"> 7874.00 </capacity>
     <contents unit="LBS"> 3937.00 </contents>
  </tank>

  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 600.40 </x>
       <y>   0.00 </y>
       <z> -29.37 </z>
     </location>
     <capacity unit="LBS"> 7874.00 </capacity>
     <contents unit="LBS"> 3937.00 </contents>
  </tank>

  <tank type="FUEL" number="3">
     <location unit="IN">
       <x> 600.40 </x>
       <y>   0.00 </y>
       <z> -29.37 </z>
     </location>
     <capacity unit="LBS"> 7874.00 </capacity>
     <contents unit="LBS"> 3937.00 </contents>
  </tank>

  <tank type="FUEL" number="4">
     <location unit="IN">
       <x> 600.40 </x>
       <y>   0.00 </y>
       <z> -29.37 </z>
     </location>
     <capacity unit="LBS"> 7874.00 </capacity>
     <contents unit="LBS"> 3937.00 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: C-130JJSBsim">

  <channel name="Pitch">

   <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>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Roll">

   <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>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/left-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="Right Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="left aileron normalization">
      <input>fcs/left-aileron-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="right aileron normalization">
      <input>fcs/right-aileron-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <property value="1">fcs/yaw-damper-enable</property>
  <channel name="Yaw">

   <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>

   <scheduled_gain name="Yaw Damper Rate">
      <input>velocities/r-aero-rad_sec</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
         <tableData>
            30     0.00
            60     2.00
         </tableData>
      </table>
      <gain>fcs/yaw-damper-enable</gain>
   </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-rate</input>
      <clipto>
        <min> -1.1 </min>
        <max>  1.1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <domain>
        <min> -2.1 </min>
        <max>  2.1 </max>
      </domain>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Flaps">
   <kinematic name="Flaps Control">
     <input>fcs/flap-cmd-norm</input>
     <traverse>
       <setting>
          <position>  0 </position>
          <time>      0 </time>
       </setting>
       <setting>
          <position> 15 </position>
          <time>      4 </time>
       </setting>
       <setting>
          <position> 30 </position>
          <time>      3 </time>
       </setting>
     </traverse>
     <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="flap normalization">
      <input>fcs/flap-pos-deg</input>
      <domain>
        <min>  0 </min>
        <max> 30 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1.5 </max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>

  </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>

<kinematic name="names/nose-wheel-steering/kinematic-norm">
<input>fcs/steer-cmd-norm</input>
<traverse>
<setting>
<position>-1.0</position>
<time>0.0</time>
</setting>
<setting>
<position>1.0</position>
<time>0.5</time>
</setting>
</traverse>
<output>gear/unit[0]/nose-wheel-steering/kinematic-norm</output>
</kinematic>

<scheduled_gain name="names/nose-wheel-steering/steer-pos-deg">
<input>gear/unit[0]/nose-wheel-steering/kinematic-norm</input>
<table>
<independentVar>velocities/vg-fps</independentVar>
<tableData><!-- note that this is positive also when moving in reverse -->
5.0 5.00
10.0 10.00
15.0 20.00
20.0 30.00
25.0 30.00
30.0 30.00
35.0 20.00
50.0 15.00
100.0 1.50
150.0 0.75
200.0 0.50 <!-- by this speed the front wheel hardly touches the runway -->
</tableData>
</table>
<output>fcs/steer-pos-deg</output>
</scheduled_gain>

  </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>

 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

    <function name="aero/force/Lift_alpha">
      <description>Lift due to alpha</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -0.20 -0.740
               0.00  0.440
               0.24  1.400
               0.60  0.904
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/force/Lift_flap">
       <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> 0.03500 </value>
       </product>
    </function>

    <function name="aero/force/Lift_speedbrake">
       <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</value>
       </product>
    </function>

    <function name="aero/force/Lift_elevator">
       <description>Lift due to Elevator Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-rad</property>
           <value>0.35</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/force/Drag_basic">
       <description>Drag at zero lift</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -1.57    1.500
             -0.26    0.023
              0.00    0.005
              0.26    0.025
              1.57    0.500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_induced">
       <description>Induced drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.029</value>
         </product>
    </function>

    <function name="aero/force/Drag_mach">
       <description>Drag due to mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.7       0.005
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/force/Drag_flap">
       <description>Drag due to flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.00117 </value>
         </product>
    </function>

    <function name="aero/force/Drag_gear">
       <description>Drag due to gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.013</value>
         </product>
    </function>

    <function name="aero/force/Drag_speedbrake">
       <description>Drag due to speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0.015</value>
         </product>
    </function>

    <function name="aero/force/Drag_beta">
       <description>Drag due to sideslip</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57    1.230
              -0.26    0.050
               0.00    0.000
               0.26    0.050
               1.57    1.230
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_elevator">
       <description>Drag due to Elevator Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.01</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/force/Side_beta">
       <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</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/moment/Roll_beta">
       <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>-0.1</value>
       </product>
    </function>

    <function name="aero/moment/Roll_damp">
       <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>-0.4</value>
       </product>
    </function>

    <function name="aero/moment/Roll_yaw">
       <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>0.15</value>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron">
       <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>
          <value>0.15</value>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder">
       <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>0.01</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/moment/Pitch_alpha">
       <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>-0.4</value>
       </product>
    </function>

    <function name="aero/moment/Pitch_elevator">
       <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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.000
              2.0     -0.250
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_damp">
       <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>-22</value>
       </product>
    </function>

    <function name="aero/moment/Pitch_alphadot">
       <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>-8</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <function name="aero/moment/Yaw_beta">
       <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>0.12</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_damp">
       <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>-0.15</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_rudder">
       <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>-0.1</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_aileron">
       <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>-0.008</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

 <external_reactions>
 </external_reactions>

</fdm_config>