<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="dc8-63" 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 0.91 </author>
  <filecreationdate> 2010-01-23 </filecreationdate>
  <version>$Revision: 1.10 $</version>
  <description> Models a dc8-63. </description>
 </fileheader>

<!--
  File:     dc8-63.xml
  Inputs:
    name:          dc8-63
    type:          four-engine transonic transport
    max weight:    355066 lb
    wing span:     148.4 ft
    length:        183 ft
    wing area:     2927 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   turbine
    engine layout: wings
    yaw damper?    yes
  Outputs:
    wing loading:  121.31 lb/sq-ft
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.2
    CD-0:          0.017
    K:             0.042

-->

 <metrics>
   <wingarea  unit="FT2"> 2927.00 </wingarea>
   <wingspan  unit="FT" >  148.40 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   19.72 </chord>
   <htailarea unit="FT2">  731.75 </htailarea>
   <htailarm  unit="FT" >   82.35 </htailarm>
   <vtailarea unit="FT2">  585.40 </vtailarea>
   <vtailarm  unit="FT" >   82.35 </vtailarm>
   <location name="AERORP" unit="M">
     <x> 0.00 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="M">
     <x> -25.548 </x>
     <y> -0.276 </y>
     <z>  -1.225 </z>
   </location>
   <location name="VRP" unit="M">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">   3730029 </ixx>
   <iyy unit="SLUG*FT2">   6403309 </iyy>
   <izz unit="SLUG*FT2">  10031947 </izz>
   <emptywt unit="LBS" >    149200 </emptywt>
   <location name="CG" unit="IN">
     <x> -5.079 </x>
     <y>   0.00 </y>
     <z> -3.568 </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="M">
     <x> -23.604 </x>
     <y>   0.00 </y>
     <z> -6.338 </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">      106519.80 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 35506.60 </damping_coeff>
   <max_steer unit="DEG"> 67.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="M">
     <x> 0.585 </x>
     <y> -3.311 </y>
     <z> -6.691 </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">      355066.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 71013.20 </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="M">
     <x> 0.585 </x>
     <y> 3.311 </y>
     <z> -6.691 </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">      355066.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 71013.20 </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="M">
     <x> -3.097 </x>
     <y> -1.717 </y>
     <z> -3.938 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      355066.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 71013.20 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="M">
     <x> -3.097 </x>
     <y> 1.717 </y>
     <z> -3.938 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      355066.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 71013.20 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="JT3D">
    <location unit="M">
      <x> -1.967 </x>
      <y> -14.391 </y>
      <z> -4.053 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>4</feed>
    <feed>1</feed>
    <feed>2</feed>
    <feed>3</feed>
    <feed>5</feed>
    <feed>6</feed>
    <feed>7</feed>
    <thruster file="direct">
     <location unit="M">
       <x> 1.729 </x>
       <y> -14.382 </y>
       <z> -3.980 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="JT3D">
    <location unit="M">
      <x> -5.494 </x>
      <y> -8.103 </y>
      <z> -4.839 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>6</feed>
    <feed>0</feed>
    <feed>2</feed>
    <feed>3</feed>
    <feed>4</feed>
    <feed>5</feed>
    <feed>7</feed>
    <thruster file="direct">
     <location unit="M">
       <x> -1.798 </x>
       <y> -8.094 </y>
       <z> -4.766 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="JT3D">
    <location unit="M">
      <x> -5.494 </x>
      <y> 8.103 </y>
      <z> -4.839 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>2</feed>
    <feed>6</feed>
    <feed>0</feed>
    <feed>1</feed>
    <feed>3</feed>
    <feed>4</feed>
    <feed>5</feed>
    <feed>7</feed>
    <thruster file="direct">
     <location unit="M">
       <x> -1.798 </x>
       <y> 8.094 </y>
       <z> -4.766 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="JT3D">
    <location unit="M">
      <x> -1.967 </x>
      <y> 14.391 </y>
      <z> -4.053 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>3</feed>
    <feed>5</feed>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <feed>4</feed>
    <feed>6</feed>
    <feed>7</feed>
    <thruster file="direct">
     <location unit="M">
       <x> 1.729 </x>
       <y> 14.382 </y>
       <z> -3.980 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!--
 Tank # : Real tank
 0:1 main
 1:2 main
 2:3 main
 3:4 main 
 4:1 alt
 5:4 alt
 6:center
 7:aux
-->

  <tank type="FUEL" number="0">
     <location unit="M">
       <x> 0.129 </x>
       <y>   -9.488 </y>
       <z> -2.664 </z>
     </location>
     <capacity unit="LBS"> 20033 </capacity>
     <contents unit="LBS"> 10000 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="M">
       <x> -3.708 </x>
       <y>   -4.546 </y>
       <z> -3.045 </z>
     </location>
     <capacity unit="LBS"> 30383 </capacity>
     <contents unit="LBS"> 15000 </contents>
  </tank>

  <tank type="FUEL" number="2">
     <location unit="M">
       <x> -3.708 </x>
       <y>   4.546 </y>
       <z> -3.045 </z>
     </location>
     <capacity unit="LBS"> 30383 </capacity>
     <contents unit="LBS"> 15000 </contents>
  </tank>

  <tank type="FUEL" number="3">
     <location unit="M">
       <x> 0.129 </x>
       <y>   9.488 </y>
       <z> -2.664 </z>
     </location>
     <capacity unit="LBS"> 20033 </capacity>
     <contents unit="LBS"> 10000 </contents>
  </tank>

  <tank type="FUEL" number="4">
     <location unit="M">
       <x> 2.922 </x>
       <y>   -15.719 </y>
       <z> -2.155 </z>
     </location>
     <capacity unit="LBS"> 11207 </capacity>
     <contents unit="LBS"> 5000 </contents>
  </tank>
  <tank type="FUEL" number="5">
     <location unit="M">
       <x> 2.922 </x>
       <y>   15.719 </y>
       <z> -2.155 </z>
     </location>
     <capacity unit="LBS"> 11207 </capacity>
     <contents unit="LBS"> 5000 </contents>
  </tank>
  <tank type="FUEL" number="6">
     <location unit="M">
       <x> -3.632 </x>
       <y>   0.00 </y>
       <z> -4.504 </z>
     </location>
     <capacity unit="LBS"> 28507 </capacity>
     <contents unit="LBS"> 14000 </contents>
  </tank>
  <tank type="FUEL" number="7">
     <location unit="M">
       <x> -5.898 </x>
       <y>   0.00 </y>
       <z> -4.103 </z>
     </location>
     <capacity unit="LBS"> 13683 </capacity>
     <contents unit="LBS"> 6500 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: dc8-63">

  <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>

  <channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.35 </min>
        <max>  0.35 </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>
   </scheduled_gain>

   <scheduled_gain name="Yaw Damper Beta">
      <input>aero/beta-rad</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30     0.00
           60     0.00
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Yaw Damper Sum">
      <input>fcs/yaw-damper-beta</input>
      <input>fcs/yaw-damper-rate</input>
      <clipto>
        <min> -0.1 </min>
        <max>  0.1 </max>
      </clipto>
   </summer>

   <scheduled_gain name="Yaw Damper Final">
      <input>fcs/yaw-damper-sum</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           30         0.0
           31         1.0
        </tableData>
      </table>
   </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-final</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <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> 12 </position>
          <time>      4 </time>
       </setting>
       <setting>
          <position> 18 </position>
          <time>      2 </time>
       </setting>
       <setting>
          <position> 23 </position>
          <time>      3 </time>
       </setting>
       <setting>
          <position> 35 </position>
          <time>      4 </time>
       </setting>
       <setting>
          <position> 50 </position>
          <time>      5 </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> 50 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </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>

  </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/coefficient/CLalpha">
      <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 -0.680
               0.00 0.200
             0.23    1.200
               0.60 0.600
            </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> 0.02000 </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>-0.08</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>
           <property>fcs/elevator-pos-rad</property>
           <value>0.2</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/coefficient/CD0">
       <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    0.022
              0.00    0.017
              0.26    0.022
              1.57       1.500
            </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>0.042</value>
         </product>
    </function>

    <function name="aero/coefficient/CDmach">
       <description>Drag_due_to_mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.79      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </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> 0.0040 </value>
         </product>
    </function>

    <function name="aero/coefficient/CDgear">
       <description>Drag_due_to_gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.011</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>0.017</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 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/coefficient/CDde">
       <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>0.04</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>-1</value>
       </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>-0.1</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>-0.4</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>0.15</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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.100
              2.0    0.033
            </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>0.01</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>-0.7</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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.300
              2.0     -0.325
            </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>-21</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>-4</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>0.12</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>-0.15</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>-0.1</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</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>

