f22-jsbsim.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="f22-jsbsim" 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 0.96, ncc_42 </author>
  <filecreationdate>2017-10-19</filecreationdate>
  <version>$Revision: 1.40 $</version>
  <description> Models an F-22A. </description>
 </fileheader>

<!--
  File:     f22-jsbsim.xml
  Inputs:
    name:          f22-jsbsim
    type:          two-engine transonic/supersonic fighter
    max weight:    83500 lb
    wing span:     44.5 ft
    length:        62 ft
    wing area:     840 sq-ft
    gear type:     tricycle
    castering:     
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage

-->

 <metrics>
   <wingarea  unit="FT2">  840.00 </wingarea>
   <wingspan  unit="FT" >   44.50 </wingspan>
   <wing_incidence>          0.00 </wing_incidence>
   <chord     unit="FT" >   18.88 </chord>
   <htailarea unit="FT2">   71.20 </htailarea>
   <htailarm  unit="FT" >   16.00 </htailarm>
   <vtailarea unit="FT2">   21.20 </vtailarea>
   <vtailarm  unit="FT" >    9.59 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 405.1  </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 160.0  </x>
     <y>   0.00 </y>
     <z>  48.71 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>380</x>
     <y>0</y>
     <z>31</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">     56039 </ixx>
   <iyy unit="SLUG*FT2">    149525 </iyy>
   <izz unit="SLUG*FT2">    160391 </izz>
   <emptywt unit="LBS" >     43340 </emptywt>
   <location name="CG" unit="IN">
     <x> 426.1  </x>
     <y>   0.00 </y>
     <z>   0    </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 223.6  </x>
     <y>   0    </y>
     <z> -79.28 </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">      25050.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 12525.00 </damping_coeff>
   <max_steer unit="DEG"> 5.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
  </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 443.5  </x>
     <y> -69.2  </y>
     <z> -78.28 </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">      83500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 41750.00 </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> 443.5  </x>
     <y>  69.2  </y>
     <z> -78.28 </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">      83500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 41750.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
  </contact>

  <contact type="STRUCTURE" name="RADOME_NOSE">
    <location unit="IN">
     <x>   0    </x>
     <y>   0    </y>
     <z>   0    </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      41750.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 4175.00  </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING_TIP_FRONT">
    <location unit="IN">
     <x> 500.5  </x>
     <y> 534    </y>
     <z>   0    </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      41750.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 4175.00  </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="LEFT_WING_TIP_FRONT">
    <location unit="IN">
     <x> 500.5  </x>
     <y>-534    </y>
     <z>   0    </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      41750.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 4175.00  </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_STAB_TIP_CENTRE">
    <location unit="IN">
     <x> 652.0   </x>
     <y> 174.5   </y>
     <z> 5.218   </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      41750.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 4175.00  </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="LEFT_STAB_TIP_CENTRE">
    <location unit="IN">
     <x> 652.0   </x>
     <y>-174.5   </y>
     <z> 5.218   </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      41750.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 4175.00  </damping_coeff>
  </contact>

 </ground_reactions>

 <propulsion>

   <engine file="F119-PW-100">
    <location unit="IN">
      <x> 594.5  </x>
      <y> -24.92 </y>
      <z>   0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 594.5  </x>
       <y> -24.92 </y>
       <z>   0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="F119-PW-100">
    <location unit="IN">
      <x> 594.5  </x>
      <y>  24.92 </y>
      <z>   0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 594.5  </x>
       <y>  24.92 </y>
       <z>   0.00 </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> 426.1  </x>
       <y> -24.92 </y>
       <z>   0    </z>
     </location>
     <capacity unit="LBS"> 9000.00 </capacity>
     <contents unit="LBS"> 9000.00 </contents> <!-- 8421 -->
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 426.1  </x>
       <y>  24.92 </y>
       <z>   0    </z>
     </location>
     <capacity unit="LBS"> 9000.00 </capacity>
     <contents unit="LBS"> 9000.00 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: f22a">

   <function name="fcs/cqbar-psf"> <!-- calibrated qbar -->
    <sum>
     <product>
      <property>aero/qbar-psf</property>
      <table>
       <independentVar lookup="row">aero/qbar-psf</independentVar>
       <tableData>
         0.0  0
         0.4  1
       </tableData>
      </table>
     </product>
     <table>
      <independentVar lookup="row">aero/qbar-psf</independentVar>
      <tableData>
        0.0  0.4
        0.4  0.0
      </tableData>
     </table>
    </sum>
   </function>

   <function name="fcs/tv-coefficient-low-alpha">
    <table>
     <independentVar lookup="row">velocities/ve-kts</independentVar>
     <tableData>
      200 1
      225 0
     </tableData>
    </table>
   </function>

   <function name="fcs/tv-coefficient-high-alpha">
    <table>
     <independentVar lookup="row">atmosphere/density-altitude</independentVar>
     <independentVar lookup="column">velocities/mach</independentVar>
     <tableData>
            0.00 0.53 0.73 0.93 1.33 2.32
      00000 1.00 1.00 0.00 0.00 0.00 0.00
      26000 1.00 1.00 1.00 0.00 0.00 0.00
      32000 1.00 1.00 1.00 1.00 0.00 0.00
      47000 1.00 1.00 1.00 1.00 0.71 0.00
     </tableData>
    </table>
   </function>

   <function name="fcs/tv-coefficient">
    <product>
     <difference>
      <value>1</value>
      <property>gear/gear-cmd-norm</property>
     </difference>

     <sum>
      <product>
       <property>fcs/tv-coefficient-low-alpha</property>
       <table>
        <independentVar lookup="row">aero/alpha-deg</independentVar>
        <tableData>
         -20 0
         -12 1
          12 1
          20 0
        </tableData>
       </table>
      </product>
      <product>
       <property>fcs/tv-coefficient-high-alpha</property>
       <table>
        <independentVar lookup="row">aero/alpha-deg</independentVar>
        <tableData>
         -20 1
         -12 0
          12 0
          20 1
        </tableData>
       </table>
      </product>
     </sum>

    </product>
   </function>

   <function name="fcs/flap-cmd-gear">
    <product>
     <property>gear/gear-cmd-norm</property>
     <table>
      <independentVar lookup="row">velocities/ve-kts</independentVar>
      <tableData>
       300  1
       350  0
      </tableData>
     </table>
    </product>
   </function>

   <function name="fcs/flap-cmd-alpha">
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <independentVar lookup="column">velocities/ve-kts</independentVar>
     <tableData>
           0     300  350  500   600
        0  0.00  0.00 0.00 0.00  0.00
        2  0.10  0.10 0.10 0.00  0.00
        5  0.20  0.20 0.20 0.00  0.00
       17  0.29  0.29 0.29 0.20  0.00
       25  0.57  0.57 0.57 0.57  0.00
       35  0.86  0.57 0.57 0.57  0.00
     </tableData>
    </table>
   </function>

   <function name="fcs/flaperon-brake-cmd"> <!-- speedbrake coefficients yet to be fine-tuned -->
    <product>
     <property>fcs/speedbrake-cmd-norm</property>
     <value>1.0</value>
     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <independentVar lookup="column">velocities/ve-kts</independentVar>
      <independentVar lookup="table">fcs/flap-cmd-gear</independentVar>
      <tableData breakPoint="0">
          0    300  500  600
        0 1.00 1.00 1.00 1.00
        2 1.00 1.00 1.00 1.00
        5 1.00 1.00 1.00 1.00
       17 1.00 1.00 1.00 1.00
       25 1.00 1.00 1.00 1.00
      </tableData>
     </table>
    </product>
   </function>

   <function name="fcs/lef-cmd-alpha">
    <product>
     <atan>
      <product>
       <tan>
        <property>aero/alpha-rad</property>
       </tan>
       <value>0.743</value>
      </product>
     </atan>
     <value>-57.3</value>
    </product>
   </function>

   <function name="fcs/symmetric-lef-cmd">
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <independentVar lookup="column">velocities/ve-kts</independentVar>
     <independentVar lookup="table">fcs/flap-cmd-gear</independentVar>
     <tableData breakPoint="0">
            0   1
        0   0   0
        1   0   0
     </tableData>
     <tableData breakPoint="1">
            0   1
        0 -35 -35
        1 -35 -35
     </tableData>
    </table>
   </function>

   <function name="fcs/symmetric-aileron-cmd">
    <table>
     <independentVar lookup="row">accelerations/Nz</independentVar>
     <independentVar lookup="column">aero/alpha-deg</independentVar>
     <independentVar lookup="table">fcs/flap-cmd-gear</independentVar>
     <tableData breakPoint="0">
            0    25
       0.0  0.0  0.2
       7.0  0.0  0.2
       7.5  0.0  0.0
       9.0  0.0 -0.4
       9.2 -1.0 -1.0
     </tableData>
     <tableData breakPoint="1">
            0    25
       0.0  0.4  0.4
       7.0  0.4  0.4
       7.5  0.0  0.0
       9.0  0.0 -0.4
       9.2 -1.0 -1.0
     </tableData>
    </table>
   </function>

   <function name="fcs/aileron-brake-cmd">
    <product>
     <property>fcs/speedbrake-cmd-norm</property>
     <value>-1.0</value>
     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <tableData>
        0  1.0
      </tableData>
     </table>
    </product>
   </function>

   <function name="fcs/rudder-brake-cmd">
    <product>
     <property>fcs/speedbrake-cmd-norm</property>
     <value>1.0</value>
     <table>
      <independentVar lookup="row">aero/beta-deg</independentVar>
      <independentVar lookup="column">aero/alpha-deg</independentVar>
      <tableData>
             0   25
       -12.0 1.0 1.0
        12.0 1.0 1.0
      </tableData>
     </table>
    </product>
   </function>

   <function name="fcs/pitch-rate-cmd-g">
    <product>
     <sum>

      <product>
       <property>velocities/vt-fps</property>
       <table>
        <independentVar lookup="row">velocities/vt-fps</independentVar>
        <tableData>
          631  0
          632  1
        </tableData>
       </table>
      </product>

      <table>
       <independentVar lookup="row">velocities/vt-fps</independentVar>
       <tableData>
         631  631
         632  0
       </tableData>
      </table>

     </sum>
     <property>velocities/q-rad_sec</property>
     <value>0.0310809502</value>

    </product>
   </function>

   <function name="fcs/Nz-gravity">
    <product>
     <cos>
      <property>attitude/pitch-rad</property>
     </cos>
     <cos>
      <property>attitude/roll-rad</property>
     </cos>
    </product>
   </function>

   <function name="fcs/pitch-limit">
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <independentVar lookup="column">accelerations/Nz</independentVar>
     <independentVar lookup="table">gear/gear-cmd-norm</independentVar>
     <tableData breakPoint="0">
          -3.5 -3.0  9.0  9.5
      -75 -1.0  0.0  0.0  0.5
      -60 -1.0  0.0  0.0  0.5
        0 -1.0  0.0  0.0  0.5
       60 -1.0  0.0  0.0  0.5
       75 -1.0  0.0  0.0  0.5
     </tableData>
     <tableData breakPoint="1">
          -3.5 -3.0  9.0  9.5
      -45 -1.0 -1.0 -1.0  0.5
      -35 -1.0  0.0  0.0  0.5
        0 -1.0  0.0  0.0  0.5
       35 -1.0  0.0  0.0  0.5
       45 -1.0  1.0  1.0  1.0
     </tableData>
    </table>
   </function>

   <function name="fcs/pitch-cmd-comp">
    <product>
     <property>aero/qbar-psf</property>
     <value>840</value>
     <sum>
      <property>aero/coefficients/moments/Pitch</property>

      <product>
       <value>1.75</value>
       <cos><property>aero/alpha-rad</property></cos>
       <property>aero/coefficients/Lift</property>
      </product>

      <product>
       <value>1.75</value>
       <sin><property>aero/alpha-rad</property></sin>
       <property>aero/coefficients/Drag</property>
      </product>

     </sum>
    </product>
   </function>

   <function name="fcs/pitch-cmd-input-rate">
    <product>
    <difference>
     <table>
      <independentVar lookup="row">fcs/elevator-cmd-norm</independentVar>
      <independentVar lookup="column">fcs/pitch-limit</independentVar>
      <independentVar lookup="table">fcs/Nz-gravity</independentVar>
      <tableData breakPoint="-1">
           -1.0   0.0   1.0
       -1  10.0  10.0   0.0
        0   0.0   0.0   0.0
        1   0.0  -2.0  -2.0
      </tableData>
      <tableData breakPoint="0">
           -1.0   0.0   1.0
       -1   9.0   9.0   0.0
        0   0.0   0.0   0.0
        1   0.0  -3.0  -3.0
      </tableData>
      <tableData breakPoint="1">
          -1.0   0.0   1.0
       -1  8.0   8.0   0.0
        0  0.0   0.0   0.0
        1  0.0  -4.0  -4.0
      </tableData>
     </table>
     <property>fcs/pitch-rate-cmd-g</property>
    </difference>

    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <independentVar lookup="column">velocities/vt-fps</independentVar>
     <independentVar lookup="table">gear/gear-cmd-norm</independentVar>
     <tableData breakPoint="0">
           631 632
         0 1.0 0.4
        35 1.0 0.4
        45 1.0 1.0
     </tableData>
     <tableData breakPoint="1">
           631 632
         0 1.0 0.2
        35 1.0 0.2
        45 1.0 1.0
     </tableData>
    </table>
    <value>-149525</value>
    </product>
   </function>

   <function name="fcs/pitch-cmd-input-g">
    <product>
    <difference>
     <sum>
      <table>
       <independentVar lookup="row">fcs/elevator-cmd-norm</independentVar>
       <tableData>
        -1  9
         0  0
         1 -3
       </tableData>
      </table>
      <product>
       <property>fcs/Nz-gravity</property>
       <table>
        <independentVar lookup="row">fcs/elevator-cmd-norm</independentVar>
        <tableData>
         -1  0
          0  1
          1  0
        </tableData>
       </table>
      </product>
     </sum>
     <property>accelerations/Nz</property>
    </difference>

    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <independentVar lookup="column">velocities/vt-fps</independentVar>
     <tableData>
           631 664
         0 0.0 0.8
        35 0.0 0.8
        45 0.0 0.0
     </tableData>
    </table>
    <value>-149525</value>
    </product>
   </function>

   <function name="fcs/pitch-cmd-input-alpha"> <!-- landing mode, currently unused -->
    <product>
    <difference>
     <table>
      <independentVar lookup="row">fcs/elevator-cmd-norm</independentVar>
      <independentVar lookup="column">fcs/pitch-limit</independentVar>
      <tableData>
           -1.0   0.0   1.0
       -1  24.0  24.0  24.0
        0  12.0  12.0  12.0
        1   0.0   0.0   0.0
      </tableData>
     </table>
     <property>aero/alpha-deg</property>
    </difference>

    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <independentVar lookup="column">velocities/vt-fps</independentVar>
     <independentVar lookup="table">gear/gear-cmd-norm</independentVar>
     <tableData breakPoint="0">
           0   1
         0 0.0 0.0
         1 0.0 0.0
     </tableData>
     <tableData breakPoint="1">
           631 632
         0 0.0 0.0
        35 0.0 0.0
        45 0.0 0.0
     </tableData>
    </table>
    <value>-149525</value>
    </product>
   </function>

   <function name="fcs/pitch-cmd-effect">
    <sum>

     <product>
      <property>fcs/cqbar-psf</property>
      <value>840</value>
      <sum>
       <table>
        <independentVar lookup="row">velocities/mach</independentVar>
        <tableData>
          0   6.5
          2   2.0
        </tableData>
       </table>
       <product>
        <cos>
         <property>aero/alpha-rad</property>
        </cos>
        <value>0</value>
        <value>-0.105</value>
       </product>
      <value>0</value>
      </sum>
     </product>

     <product>
      <sum>
       <property>propulsion/engine[0]/thrust-lbs</property>
       <property>propulsion/engine[1]/thrust-lbs</property>
      </sum>
      <value>15</value>
      <property>fcs/tv-coefficient</property>
     </product>

    </sum>
   </function>

   <function name="fcs/pitch-cmd">
    <quotient>
     <sum>
      <property>fcs/pitch-cmd-comp</property>
      <property>fcs/pitch-cmd-input-rate</property>
      <property>fcs/pitch-cmd-input-g</property>
      <property>fcs/pitch-cmd-input-alpha</property>
     </sum>
     <property>fcs/pitch-cmd-effect</property>
    </quotient>
   </function>

   <function name="fcs/roll-cmd-comp">
    <product>
     <property>fcs/cqbar-psf</property>
     <value>840</value>
     <sum>

      <property>aero/coefficients/moments/Roll</property>

     </sum>
    </product>
   </function>

   <function name="fcs/thrust-vector-sum-corrected">
    <product>
     <property>fcs/thrust-vector-sum</property>
     <property>fcs/tv-coefficient</property>
    </product>
   </function>

   <function name="fcs/roll-cmd-input-rate">
    <product>
    <difference>
     <product>
      <value>0.01745</value>
      <table>
       <independentVar lookup="row">fcs/aileron-cmd-norm</independentVar>
       <independentVar lookup="column">aero/alpha-deg</independentVar>
       <tableData>
              -60  -45  -40  -35  -25  -20  -16  -12   -8   -4    0    4    8   12   16   20   25   35   40   45   60
        -1.0  -20  -30  -40  -50  -85 -105 -130 -140 -190 -200 -200 -200 -190 -140 -130 -105  -85  -50  -40  -30  -20
         0.0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0    0
         1.0   20   30   40   50   85  105  130  140  190  200  200  200  190  140  130  105   85   50   40   30   20
       </tableData>
      </table>
     </product>
     <property>velocities/p-rad_sec</property>
    </difference>
    <value>-560390</value>
    </product>
   </function>

   <function name="fcs/roll-cmd-effect">
    <sum>

     <product> <!-- aileron -->
      <property>fcs/cqbar-psf</property>
      <value>840</value>
      <table>
       <independentVar lookup="row">aero/alpha-deg</independentVar>
       <tableData>
        -17 -1.00125
         0  -2.22500
         50 -1.00125
       </tableData>
      </table>
      <table>
       <independentVar lookup="row">fcs/speedbrake-cmd-norm</independentVar>
       <tableData>
         0 1.0
         1 0.5
       </tableData>
      </table>
     </product>

     <product> <!-- flaperon -->
      <property>fcs/cqbar-psf</property>
      <value>840</value>
      <property>fcs/differential-flaperon-factor</property>
      <table>
       <independentVar lookup="row">aero/alpha-deg</independentVar>
       <tableData>
        -17    -3.213265
         0     -7.140595
         50    -3.213265
       </tableData>
      </table>
      <table>
       <independentVar lookup="row">fcs/speedbrake-cmd-norm</independentVar>
       <tableData>
         0 1.0
         1 0.5
       </tableData>
      </table>
     </product>

     <product> <!-- stabilator -->
      <property>fcs/cqbar-psf</property>
      <value>840</value>
      <property>fcs/differential-stabilator-factor</property>
      <table>
       <independentVar lookup="row">aero/alpha-deg</independentVar>
       <tableData>
         0 -1.39975
       </tableData>
      </table>
     </product>

    </sum>
   </function>

   <function name="fcs/roll-cmd">
    <quotient>
     <sum>
      <property>fcs/roll-cmd-comp</property>
      <property>fcs/roll-cmd-input-rate</property>
     </sum>
     <property>fcs/roll-cmd-effect</property>
    </quotient>
   </function>

   <function name="fcs/differential-stabilator-factor">
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
      <tableData>
        0   1.0
     </tableData>
    </table>
   </function>

   <function name="fcs/differential-flaperon-factor">
    <table>
     <independentVar lookup="row">fcs/flap-cmd-gear</independentVar>
      <tableData>
        0  1.0
        1  0.0
     </tableData>
    </table>
   </function>

   <function name="fcs/right-aileron-roll-cmd">
    <product>
     <property>fcs/roll-cmd</property>
     <value>-1</value>
    </product>
   </function>

   <function name="fcs/left-aileron-roll-cmd">
    <product>
     <property>fcs/roll-cmd</property>
     <value>1</value>
    </product>
   </function>

   <function name="fcs/right-flaperon-roll-cmd">
    <product>
     <property>fcs/roll-cmd</property>
     <property>fcs/differential-flaperon-factor</property>
     <value>-1</value>
    </product>
   </function>

   <function name="fcs/left-flaperon-roll-cmd">
    <product>
     <property>fcs/roll-cmd</property>
     <property>fcs/differential-flaperon-factor</property>
     <value>1</value>
    </product>
   </function>

   <function name="fcs/right-stab-roll-cmd">
    <product>
     <property>fcs/roll-cmd</property>
     <property>fcs/differential-stabilator-factor</property>
     <value>-1</value>
    </product>
   </function>

   <function name="fcs/left-stab-roll-cmd">
    <product>
     <property>fcs/roll-cmd</property>
     <property>fcs/differential-stabilator-factor</property>
     <value>1</value>
    </product>
   </function>

   <function name="fcs/yaw-cmd-comp">
    <product>
     <property>fcs/cqbar-psf</property>
     <value>840</value>
     <sum>

      <property>aero/coefficients/moments/Yaw</property>

      <product> <!-- side force -->
       <value>1.75</value>
       <table>
        <independentVar lookup="row">aero/beta-deg</independentVar>
        <independentVar lookup="column">aero/alpha-deg</independentVar>
        <tableData>
             -90   -17    0     17    90
         -45  0.00  0.50  0.66  0.50  0.00
         -20  0.00  0.24  0.32  0.24  0.00
         -12  0.00  0.16  0.21  0.16  0.00
           0  0.00  0.00  0.00  0.00  0.00
          12  0.00 -0.16 -0.21 -0.16  0.00
          20  0.00 -0.24 -0.32 -0.24  0.00
          45  0.00 -0.50 -0.66 -0.50  0.00
        </tableData>
       </table>
      </product>

     </sum>
    </product>
   </function>

   <function name="fcs/yaw-cmd-input-beta">
    <product>

     <table>
      <independentVar lookup="row">aero/beta-deg</independentVar>
      <tableData>
       -30 -25
       -12 -12
         0  0
        12  12
        30  25
      </tableData>
     </table>

     <table>
      <independentVar lookup="row">aero/alpha-deg</independentVar>
      <tableData>
       -90 0.0
       -60 1.0
        60 1.0
        90 0.0
      </tableData>
     </table>
     <table>
      <independentVar lookup="row">velocities/ve-kts</independentVar>
      <independentVar lookup="column">gear/wow</independentVar>
      <tableData>
           0   1
         0 1.0 0.0
        50 1.0 0.0
       100 1.0 0.1
      </tableData>
     </table>
     <value>-14952.5</value>
    </product>
   </function>

   <function name="fcs/yaw-cmd-input-rate">
    <product>
     <difference>
      <table>
       <independentVar lookup="row">fcs/rudder-cmd-norm</independentVar>
       <tableData>
        -1  0.5
         0  0.0
         1 -0.5
       </tableData>
      </table>
      <property>velocities/r-rad_sec</property>
     </difference>
     <table>
      <independentVar lookup="row">velocities/ve-kts</independentVar>
      <independentVar lookup="column">gear/wow</independentVar>
      <tableData>
           0   1
         0 1.0 0.0
        50 1.0 1.0
      </tableData>
     </table>
     <value>-149525</value>
    </product>
   </function>

   <function name="fcs/yaw-cmd-effect">
    <product>
     <property>fcs/cqbar-psf</property>
     <value>840</value>
     <table>
      <independentVar lookup="row">aero/alpha-rad</independentVar>
      <tableData>
       -2.66  -4.6725
       -1.01   0.0
        0.45   4.6725
        2.04   0.0
      </tableData>
     </table>
     <table>
      <independentVar lookup="row">fcs/speedbrake-cmd-norm</independentVar>
      <tableData>
        0 1.0
        1 0.5
      </tableData>
     </table>
    </product>
   </function>

   <function name="fcs/yaw-cmd">
    <quotient>
     <sum>
      <property>fcs/yaw-cmd-comp</property>
      <property>fcs/yaw-cmd-input-beta</property>
      <property>fcs/yaw-cmd-input-rate</property>
     </sum>
     <property>fcs/yaw-cmd-effect</property>
    </quotient>
   </function>

   <function name="fcs/right-rudder-cmd">
    <sum>
     <product>
      <property>fcs/yaw-cmd</property>
      <value>-1</value>
     </product>
     <property>fcs/rudder-brake-cmd</property>
    </sum>
   </function>

   <function name="fcs/left-rudder-cmd">
    <sum>
     <product>
      <property>fcs/yaw-cmd</property>
      <value>1</value>
     </product>
     <property>fcs/rudder-brake-cmd</property>
    </sum>
   </function>

  <channel name="Stabilators">

   <summer name="Right Stabilator Sum">
      <input>fcs/pitch-cmd</input>
      <input>fcs/right-stab-roll-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <summer name="Left Stabilator Sum">
      <input>fcs/pitch-cmd</input>
      <input>fcs/left-stab-roll-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Right Stabilator Control">
      <input>fcs/right-stabilator-sum</input>
      <range>
        <min> -1.0 </min>
        <max>  1.0 </max>
      </range>
      <output>fcs/right-stabilator-pos-deg</output>
   </aerosurface_scale>

   <aerosurface_scale name="Left Stabilator Control">
      <input>fcs/left-stabilator-sum</input>
      <range>
        <min> -1.0 </min>
        <max>  1.0 </max>
      </range>
      <output>fcs/left-stabilator-pos-deg</output>
   </aerosurface_scale>

   <kinematic name="Right Stabilator Position">
      <input>fcs/right-stabilator-pos-deg</input>
      <traverse>
        <setting>
          <position>-30</position>
          <time>0.417</time>
        </setting>
        <setting>
          <position>25</position>
          <time>0.500</time>
        </setting>
       </traverse>
      <output>fcs/right-stabilator-pos-deg2</output>
   </kinematic>

   <kinematic name="Left Stabilator Position">
      <input>fcs/left-stabilator-pos-deg</input>
      <traverse>
        <setting>
          <position>-30</position>
          <time>0.417</time>
        </setting>
        <setting>
          <position>25</position>
          <time>0.500</time>
        </setting>
       </traverse>
      <output>fcs/left-stabilator-pos-deg2</output>
   </kinematic>

   <summer name="Thrust Vector Sum">
      <input>fcs/pitch-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Thrust Vector Control">
      <input>fcs/thrust-vector-sum-corrected</input>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/tv-pos-rad</output>
   </aerosurface_scale>

   <kinematic name="TV Position">
      <input>fcs/tv-pos-rad</input>
      <traverse>
        <setting>
          <position>-0.349</position>
          <time>0.5</time>
        </setting>
        <setting>
          <position>0.349</position>
          <time>0.5</time>
        </setting>
       </traverse>
      <output>fcs/tv-pos-rad2</output>
   </kinematic>

   <aerosurface_scale name="TV normalization">
      <input>fcs/tv-pos-rad2</input>
      <domain>
        <min> -0.349 </min>
        <max>  0.349 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/tvc-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Ailerons">

   <summer name="Right Aileron Sum">
      <input>fcs/right-aileron-roll-cmd</input>
      <input>fcs/symmetric-aileron-cmd</input>
      <input>fcs/aileron-brake-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <summer name="Left Aileron Sum">
      <input>fcs/left-aileron-roll-cmd</input>
      <input>fcs/symmetric-aileron-cmd</input>
      <input>fcs/aileron-brake-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Right Aileron Control">
      <input>fcs/right-aileron-sum</input>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/right-aileron-pos-deg</output>
   </aerosurface_scale>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/left-aileron-sum</input>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-deg</output>
   </aerosurface_scale>
   
   <kinematic name="Right Aileron Position">
      <input>fcs/right-aileron-pos-deg</input>
      <traverse>
        <setting>
          <position>-25</position>
          <time>0.357</time>
        </setting>
        <setting>
          <position>25</position>
          <time>0.357</time>
        </setting>
       </traverse>
      <output>fcs/right-aileron-pos-deg2</output>
   </kinematic>
   
   <kinematic name="Left Aileron Position">
      <input>fcs/left-aileron-pos-deg</input>
      <traverse>
        <setting>
          <position>-25</position>
          <time>0.357</time>
        </setting>
        <setting>
          <position>25</position>
          <time>0.357</time>
        </setting>
       </traverse>
      <output>fcs/left-aileron-pos-deg2</output>
   </kinematic>

  </channel>

  <channel name="Flaperons">

   <summer name="Right Flaperon Sum">
      <input>fcs/flap-cmd-gear</input>
      <input>fcs/flap-cmd-alpha</input>
      <input>fcs/flaperon-brake-cmd</input>
      <input>fcs/right-flaperon-roll-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <summer name="Left Flaperon Sum">
      <input>fcs/flap-cmd-gear</input>
      <input>fcs/flap-cmd-alpha</input>
      <input>fcs/flaperon-brake-cmd</input>
      <input>fcs/left-flaperon-roll-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>
   
   <kinematic name="Right Flaperon Position">
      <input>fcs/right-flaperon-sum</input>
      <traverse>
        <setting>
          <position>-20</position>
          <time>0.286</time>
        </setting>
        <setting>
          <position>35</position>
          <time>0.5</time>
        </setting>
       </traverse>
      <output>fcs/right-flaperon-pos-deg</output>
   </kinematic>
   
   <kinematic name="Left Flaperon Position">
      <input>fcs/left-flaperon-sum</input>
      <traverse>
        <setting>
          <position>-20</position>
          <time>0.286</time>
        </setting>
        <setting>
          <position>35</position>
          <time>0.5</time>
        </setting>
       </traverse>
      <output>fcs/left-flaperon-pos-deg</output>
   </kinematic>

  </channel>

  <channel name="Rudders">

   <summer name="Right Rudder Sum">
      <input>fcs/right-rudder-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <summer name="Left Rudder Sum">
      <input>fcs/left-rudder-cmd</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Right Rudder Control">
      <input>fcs/right-rudder-sum</input>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/right-rudder-pos-deg</output>
   </aerosurface_scale>

   <aerosurface_scale name="Left Rudder Control">
      <input>fcs/left-rudder-sum</input>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-rudder-pos-deg</output>
   </aerosurface_scale>
   
   <kinematic name="Right Rudder Position">
      <input>fcs/right-rudder-pos-deg</input>
      <traverse>
        <setting>
          <position>-30</position>
          <time>0.375</time>
        </setting>
        <setting>
          <position>30</position>
          <time>0.375</time>
        </setting>
       </traverse>
      <output>fcs/right-rudder-pos-deg2</output>
   </kinematic>
   
   <kinematic name="Left Rudder Position">
      <input>fcs/left-rudder-pos-deg</input>
      <traverse>
        <setting>
          <position>-30</position>
          <time>0.375</time>
        </setting>
        <setting>
          <position>30</position>
          <time>0.375</time>
        </setting>
       </traverse>
      <output>fcs/left-rudder-pos-deg2</output>
   </kinematic>

  </channel>

  <channel>

   <scheduled_gain name="Throttle0">
    <input>fcs/throttle-cmd-norm[0]</input>
    <table>
     <independentVar>fcs/throttle-pos-norm[0]</independentVar>
     <tableData>
      0.0    0.0
      0.9    1.0
      1.0    2.0
     </tableData>
    </table>
    <output>fcs/throttle-pos-norm[0]</output>
   </scheduled_gain>

   <scheduled_gain name="Throttle1">
    <input>fcs/throttle-cmd-norm[1]</input>
    <table>
     <independentVar>fcs/throttle-pos-norm[1]</independentVar>
     <tableData>
      0.0    0.0
      0.9    1.0
      1.0    2.0
     </tableData>
    </table>
    <output>fcs/throttle-pos-norm[1]</output>
   </scheduled_gain>

  </channel>

  <channel name="Leading Edge Flaps">
  
   <summer name="Right LEF Sum">
      <input>fcs/lef-cmd-alpha</input>
      <input>fcs/symmetric-lef-cmd</input>
      <clipto>
        <min> -35 </min>
        <max>  2  </max>
      </clipto>
   </summer>
  
   <summer name="Left LEF Sum">
      <input>fcs/lef-cmd-alpha</input>
      <input>fcs/symmetric-lef-cmd</input>
      <clipto>
        <min> -35 </min>
        <max>  2  </max>
      </clipto>
   </summer>
   
   <kinematic name="Right LEF Position">
     <input>fcs/right-lef-sum</input>
     <traverse>
       <setting>
          <position> -35 </position>
          <time>      1  </time>
       </setting>
       <setting>
          <position>  2     </position>
          <time>      1 </time>
       </setting>
     </traverse>
     <output>fcs/right-lef-pos-deg</output>
   </kinematic>
   
   <kinematic name="Left LEF Position">
     <input>fcs/left-lef-sum</input>
     <traverse>
       <setting>
          <position> -35 </position>
          <time>      1  </time>
       </setting>
       <setting>
          <position>  2     </position>
          <time>      1 </time>
       </setting>
     </traverse>
     <output>fcs/left-lef-pos-deg</output>
   </kinematic>

  </channel>

  <channel name="Landing Gear">
   <kinematic name="Gear Control">
     <input>gear/gear-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0.00 </position>
          <time>     0.00    </time> <!-- nothing? -->
       </setting>
       <setting>
          <position> 0.25 </position>
          <time>     0.35    </time> <!-- nose doors closing: 0.35 seconds -->
       </setting>
       <setting>
          <position> 0.50 </position>
          <time>     0.75  </time> <!-- period where nose is retracting: 0.75 seconds -->
       </setting>
       <setting>
          <position> 0.75 </position>
          <time>     1    </time> <!-- main gear doors opening/closing: 1 second -->
       </setting>
       <setting>
          <position> 1.00 </position>
          <time>     1.8    </time> <!-- main gear extension/retraction: 1.8 seconds -->
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>

  </channel>

 </flight_control>

 <aerodynamics>

  <function name="aero/coefficients/Lift/Mach_factor">
   <description>Lift Mach factor</description>
   <table>
    <independentVar lookup="row">velocities/mach</independentVar>
    <tableData>
     0.00 1.00
    </tableData>
   </table>
  </function>

  <function name="aero/coefficients/Lift/alpha">
   <description>Lift by angle of attack</description>
   <table>
    <independentVar lookup="row">aero/alpha-deg</independentVar>
    <tableData>
    -90  0.00
    -40 -1.68
    -17 -1.00
      0  0.00
     35  2.10
     40  2.15
     45  2.10
     60  1.75
     90  0.10
    </tableData>
   </table>
  </function>

  <function name="aero/coefficients/Lift/flaperon_right">
   <description>Change in lift due to right flaperon deflection</description>
   <product>
    <property>fcs/right-flaperon-pos-deg</property>
    <value>0.005835</value>
   </product>
  </function>

  <function name="aero/coefficients/Lift/flaperon_left">
   <description>Change in lift due to left flaperon deflection</description>
   <product>
    <property>fcs/left-flaperon-pos-deg</property>
    <value>0.005835</value>
   </product>
  </function>

  <function name="aero/coefficients/Lift/stabilator_right">
   <description>Change in lift due to right stabilator deflection</description>
   <product>
    <property>fcs/right-stabilator-pos-deg2</property>
    <value>0.00175</value>
   </product>
  </function>

  <function name="aero/coefficients/Lift/stabilator_left">
   <description>Change in lift due to left stabilator deflection</description>
   <product>
    <property>fcs/left-stabilator-pos-deg2</property>
    <value>0.00175</value>
   </product>
  </function>

  <function name="aero/coefficients/Lift/aileron_right">
   <description>Change in lift due to right aileron deflection</description>
   <product>
    <property>fcs/right-aileron-pos-deg2</property>
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <tableData>
      -17  0.00045
        0  0.00100
       50  0.00045
     </tableData>
    </table>
   </product>
  </function>

  <function name="aero/coefficients/Lift/aileron_left">
   <description>Change in lift due to left aileron deflection</description>
   <product>
    <property>fcs/left-aileron-pos-deg2</property>
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <tableData>
      -17  0.00045
        0  0.00100
       50  0.00045
     </tableData>
    </table>
   </product>
  </function>

  <function name="aero/coefficients/Lift">
   <product>
    <property>aero/coefficients/Lift/Mach_factor</property>
    <sum>
     <property>aero/coefficients/Lift/alpha</property>
     <property>aero/coefficients/Lift/flaperon_right</property>
     <property>aero/coefficients/Lift/flaperon_left</property>
     <property>aero/coefficients/Lift/stabilator_right</property>
     <property>aero/coefficients/Lift/stabilator_left</property>
     <property>aero/coefficients/Lift/aileron_right</property>
     <property>aero/coefficients/Lift/aileron_left</property>
    </sum>
   </product>
  </function>

  <axis name="LIFT">

   <function name="aero/forces/Lift">
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>aero/coefficients/Lift</property>
    </product>
   </function>

  </axis>

  <function name="aero/coefficients/Drag/Mach_factor">
   <description>Drag factor by Mach number</description>
   <table>
    <independentVar lookup="row">velocities/mach</independentVar>
    <tableData>
     0.00 1.000
     0.85 1.000
     0.90 1.100
     1.00 2.000
     1.15 2.200
     2.00 2.200
    </tableData>
   </table>
  </function>

  <function name="aero/coefficients/Drag/zero_lift">
   <description>Zero-lift drag coefficient</description>
   <table>
    <independentVar lookup="row">aero/alpha-deg</independentVar>
    <tableData>
     -90 1.500
     -17 0.034
       0 0.019
      17 0.034
      90 1.500
    </tableData>
   </table>
  </function>

  <function name="aero/coefficients/Drag/induced">
   <description>Induced drag coefficient</description>
   <product>
    <property>aero/cl-squared</property>
    <value>0.12</value>
   </product>
  </function>

  <function name="aero/coefficients/Drag/beta">
   <description>Change in drag due to sideslip</description>
   <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>
  </function>

  <function name="aero/coefficients/Drag/Mach"> <!-- currently unused -->
   <description>Change in drag due to Mach number</description>
   <table>
    <independentVar lookup="row">velocities/mach</independentVar>
    <tableData>
     0.00 0.000
     0.90 0.000
     1.00 0.025
     1.20 0.030
     2.00 0.020
    </tableData>
   </table>
  </function>

  <function name="aero/coefficients/Drag/flaperon_right">
   <description>Change in drag due to right flaperon deflection</description>
   <product>
    <abs><property>fcs/right-flaperon-pos-deg</property></abs>
    <value>0.0025</value>
   </product>
  </function>

  <function name="aero/coefficients/Drag/flaperon_left">
   <description>Change in drag due to left flaperon deflection</description>
   <product>
    <abs><property>fcs/left-flaperon-pos-deg</property></abs>
    <value>0.0025</value>
   </product>
  </function>

  <function name="aero/coefficients/Drag/stabilator_right">
   <description>Change in drag due to right stabilator deflection</description>
   <product>
    <abs><property>fcs/right-stabilator-pos-deg2</property></abs>
    <value>0.000004</value>
   </product>
  </function>

  <function name="aero/coefficients/Drag/stabilator_left">
   <description>Change in drag due to left stabilator deflection</description>
   <product>
    <abs><property>fcs/left-stabilator-pos-deg2</property></abs>
    <value>0.000004</value>
   </product>
  </function>

  <function name="aero/coefficients/Drag/gear">
   <description>Drag due to landing gear</description>
   <product>
    <property>gear/gear-pos-norm</property>
    <value>0.009</value>
   </product>
  </function>

  <function name="aero/coefficients/Drag">
   <product>
    <property>aero/coefficients/Drag/Mach_factor</property>
    <sum>
     <property>aero/coefficients/Drag/zero_lift</property>
     <property>aero/coefficients/Drag/induced</property>
     <property>aero/coefficients/Drag/beta</property>
     <property>aero/coefficients/Drag/flaperon_right</property>
     <property>aero/coefficients/Drag/flaperon_left</property>
     <property>aero/coefficients/Drag/stabilator_right</property>
     <property>aero/coefficients/Drag/stabilator_left</property>
    </sum>
   </product>
  </function>

  <axis name="DRAG">

   <function name="aero/forces/Drag">
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>aero/coefficients/Drag</property>
    </product>
   </function>

  </axis>

  <function name="aero/coefficients/Side/beta">
   <description>Side force by to sideslip</description>
   <table>
    <independentVar lookup="row">aero/beta-deg</independentVar>
    <independentVar lookup="column">aero/alpha-deg</independentVar>
    <tableData>
         -90   -17    0     17    90
     -45  0.00  0.50  0.66  0.50  0.00
     -20  0.00  0.24  0.32  0.24  0.00
     -12  0.00  0.16  0.21  0.16  0.00
       0  0.00  0.00  0.00  0.00  0.00
      12  0.00 -0.16 -0.21 -0.16  0.00
      20  0.00 -0.24 -0.32 -0.24  0.00
      45  0.00 -0.50 -0.66 -0.50  0.00
    </tableData>
   </table>
  </function>

  <function name="aero/coefficients/Side">
   <sum>
    <property>aero/coefficients/Side/beta</property>
   </sum>
  </function>

  <axis name="SIDE">

   <function name="aero/forces/Side">
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>aero/coefficients/Side</property>
    </product>
   </function>

  </axis>

  <function name="aero/coefficients/moments/Roll/damp">
   <description>Roll damping moment</description>
   <product>
    <property>aero/bi2vel</property>
    <property>velocities/p-aero-rad_sec</property>
    <value>-17.8</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Roll/beta">
   <description>Change in roll moment due to sideslip</description>
   <product>
    <property>aero/beta-deg</property>
    <value>0.078</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Roll/yaw">
   <description>Change in roll moment due to yaw rate</description>
   <product>
    <property>aero/bi2vel</property>
    <property>velocities/r-aero-rad_sec</property>
    <value>6.7</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Roll">
   <sum>
    <property>aero/coefficients/moments/Roll/damp</property>
    <property>aero/coefficients/moments/Roll/beta</property>
    <property>aero/coefficients/moments/Roll/yaw</property>
   </sum>
  </function>

  <axis name="ROLL">

   <function name="aero/moments/Roll">
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>aero/coefficients/moments/Roll</property>
    </product>
   </function>

    <function name="aero/moment/Roll_aileron_right">
       <description>Roll moment due to right aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/right-aileron-pos-deg2</property>
          <table>
           <independentVar lookup="row">aero/alpha-deg</independentVar>
           <tableData>
            -17   -0.00045
             0    -0.00100
             50   -0.00045
           </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron_left">
       <description>Roll moment due to left aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-deg2</property>
          <table>
           <independentVar lookup="row">aero/alpha-deg</independentVar>
           <tableData>
            -17    0.00045
             0     0.00100
             50    0.00045
           </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_flaperon_right">
       <description>Roll moment due to right flaperon</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/right-flaperon-pos-deg</property>
          <table>
           <independentVar lookup="row">aero/alpha-deg</independentVar>
           <tableData>
            -17   -0.058423
             0    -0.129829
             50   -0.058423
           </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_flaperon_left">
       <description>Roll moment due to left flaperon</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/left-flaperon-pos-deg</property>
          <table>
           <independentVar lookup="row">aero/alpha-deg</independentVar>
           <tableData>
            -17    0.058423
             0     0.129829
             50    0.058423
           </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_stabilator_right">
       <description>Roll moment due to right stabilator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/right-stabilator-pos-deg2</property>
          <table>
           <independentVar lookup="row">aero/alpha-deg</independentVar>
           <tableData>
             0 -0.02545
           </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_stabilator_left">
       <description>Roll moment due to left stabilator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/left-stabilator-pos-deg2</property>
          <table>
           <independentVar lookup="row">aero/alpha-deg</independentVar>
           <tableData>
              0  0.02545
           </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder_right">
       <description>Roll moment due to right rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/right-rudder-pos-deg2</property>
           <value>-0.0037825</value>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder_left">
       <description>Roll moment due to left rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/left-rudder-pos-deg2</property>
           <value>0.0037825</value>
       </product>
    </function>

  </axis>

  <function name="aero/coefficients/moments/Pitch/alpha">
   <description>Pitch moment by angle of attack</description>
   <product>
    <property>aero/alpha-deg</property>
    <table>
     <independentVar lookup="row">aero/alpha-deg</independentVar>
     <tableData>
      -90  0.000000
        0  0.052864
       90  0.000000
     </tableData>
    </table>
   </product>
  </function>

  <function name="aero/coefficients/moments/Pitch/damp">
   <description>Pitch damping moment</description>
   <product>
    <property>aero/ci2vel</property>
    <property>velocities/q-aero-rad_sec</property>
    <value>-105.728</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Pitch/alphadot">
   <description>Change in pitch moment due to rate of change of angle of attack</description>
   <product>
    <property>aero/ci2vel</property>
    <property>aero/alphadot-rad_sec</property>
    <value>-169.92</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Pitch/flaperon_right">
   <description>Change in pitch moment due to right flaperon deflection</description>
   <product>
    <property>fcs/right-flaperon-pos-deg</property>
    <value>-0.002</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Pitch/flaperon_left">
   <description>Change in pitch moment due to left flaperon deflection</description>
   <product>
    <property>fcs/left-flaperon-pos-deg</property>
    <value>-0.002</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Pitch">
   <sum>
    <property>aero/coefficients/moments/Pitch/alpha</property>
    <property>aero/coefficients/moments/Pitch/damp</property>
    <property>aero/coefficients/moments/Pitch/alphadot</property>
    <property>aero/coefficients/moments/Pitch/flaperon_right</property>
    <property>aero/coefficients/moments/Pitch/flaperon_left</property>
   </sum>
  </function>

  <axis name="PITCH">

   <function name="aero/moments/Pitch">
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>aero/coefficients/moments/Pitch</property>
    </product>
   </function>

    <function name="aero/moment/Pitch_stabilator_right">
       <description>Pitch moment due to right stabilator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/right-stabilator-pos-deg2</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -0.13
              2.0     -0.04
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_stabilator_left">
       <description>Pitch moment due to left stabilator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/left-stabilator-pos-deg2</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -0.13
              2.0     -0.04
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_TVC">
       <description>Pitch moment due to thrust vector</description>
       <product>
          <sum>
           <property>propulsion/engine[0]/thrust-lbs</property>
           <property>propulsion/engine[1]/thrust-lbs</property>
          </sum>
          <sin>
           <property>fcs/tvc-pos-norm</property>
          </sin>
          <value>-15</value>
       </product>
    </function>

  </axis>

  <function name="aero/coefficients/moments/Yaw/beta">
   <description>Yaw moment due to sideslip</description>
   <product>
    <property>aero/beta-deg</property>
    <value>0.093</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Yaw/damp">
   <description>Yaw damping moment</description>
   <product>
    <property>aero/bi2vel</property>
    <property>velocities/r-aero-rad_sec</property>
    <value>-6.7</value>
   </product>
  </function>

  <function name="aero/coefficients/moments/Yaw">
   <sum>
    <property>aero/coefficients/moments/Yaw/beta</property>
    <property>aero/coefficients/moments/Yaw/damp</property>
   </sum>
  </function>

  <axis name="YAW">

   <function name="aero/moments/Yaw">
    <product>
     <property>aero/qbar-psf</property>
     <property>metrics/Sw-sqft</property>
     <property>aero/coefficients/moments/Yaw</property>
    </product>
   </function>

    <function name="aero/moment/Yaw_rudder_right">
       <description>Yaw moment due to right rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/right-rudder-pos-deg2</property>
           <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -2.66  -0.077875
             -1.01   0.0
              0.45   0.077875
              2.04   0.0
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Yaw_rudder_left">
       <description>Yaw moment due to left rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/left-rudder-pos-deg2</property>
           <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -2.66   0.077875
             -1.01   0.0
              0.45  -0.077875
              2.04   0.0
            </tableData>
          </table>
       </product>
    </function>

  </axis>

 </aerodynamics>

 <external_reactions>
 </external_reactions>

</fdm_config>