AvroVulcanB2/vulcanb2.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Vulcan B2" version="2.0" release="BETA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author>Stuart Buchanan</author>
  <filecreationdate> 22.03.2008 </filecreationdate>
  <version> 0.2 </version>
  <description> Models an Avro Vulcan B2. </description>
 </fileheader>

<!--
  File:     Vulcan B2.xml
  Inputs:
    name:          Vulcan B2
    type:          four-engine transonic transport
    max weight:    203962.5 lb
    wing span:     110.99623 ft
    length:        99.90645 ft
    wing area:     3965.826 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   turbine
    engine layout: middle fuselage
    yaw damper?    no

  Outputs:
    wing loading:  51.43 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"> 3965.00 </wingarea>
   <wingspan  unit="FT" >  111.00 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   35.73 </chord>
   <htailarea unit="FT2">  991.46 </htailarea>
   <htailarm  unit="FT" >   44.96 </htailarm>
   <vtailarea unit="FT2">  793.17 </vtailarea>
   <vtailarm  unit="FT" >   44.96 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 659.38 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  83.92 </x>
     <y> -32.00 </y>
     <z>  80.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x> 0.00 </x>
     <y> 0.00 </y>
     <z> 0.00 </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">   1198979 </ixx>
   <iyy unit="SLUG*FT2">   1096802 </iyy>
   <izz unit="SLUG*FT2">   2334731 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >    122378 </emptywt>
   <location name="CG" unit="IN">
     <x> 659.38 </x>
     <y>   0.00 </y>
     <z> -29.97 </z>
   </location>
   <pointmass name="dummy">
     <weight unit="LBS">1</weight>
     <location name="dumm2" unit="IN">
       <x> 659.38</x>
       <y> 0.0</y>
       <z> -29.97</z>
     </location>     
   </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 380.00 </x>
     <y>   0.00 </y>
     <z> -113.78 </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">      61188.75 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 20396.25 </damping_coeff>
   <max_steer unit="DEG"> 15.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 747.00 </x>
     <y> -189.00 </y>
     <z> -113.70 </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">      203962.50 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 40792.50 </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> 747.00 </x>
     <y>  189.00 </y>
     <z> -113.70 </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">      203962.50 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 40792.50 </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> 1054.00 </x>
     <y> -660.50 </y>
     <z> -19.70 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      203962.50 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 40792.50 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 1054.00 </x>
     <y>  660.50 </y>
     <z> -19.70 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      203962.50 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 40792.50 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="TAIL">
    <location unit="IN">
     <x> 1162.00 </x>
     <y>  0.0 </y>
     <z> -29.0   </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      203962.50 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 40792.50 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RUDDER">
    <location unit="IN">
     <x> 1164.00 </x>
     <y>  0.0 </y>
     <z> 211.0 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      203962.50 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 40792.50 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="NOSE">
    <location unit="IN">
     <x> 0.00 </x>
     <y>  0.0 </y>
     <z> 0.0 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      203962.50 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 40792.50 </damping_coeff>
 </contact>



 </ground_reactions>

 <propulsion>

   <engine file="Olympus_301">
    <location unit="IN">
      <x> 1064.00 </x>
      <y> -92.00 </y>
      <z> -58.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>3</feed>
    <feed>4</feed>
    <feed>6</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> 1064.00 </x>
      <y> -92.00 </y>
      <z> -58.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="Olympus_301">
    <location unit="IN">
      <x> 1064.00 </x>
      <y> -140.00 </y>
      <z> -58.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>2</feed>
    <feed>5</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> 1064.00 </x>
      <y> -140.00 </y>
      <z> -58.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="Olympus_301">
    <location unit="IN">
      <x> 1064.00 </x>
      <y>  92.00 </y>
      <z> -58.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>7</feed>
    <feed>10</feed>
    <feed>11</feed>
    <feed>13</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> 1064.00 </x>
      <y>  92.00 </y>
      <z> -58.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="Olympus_301">
    <location unit="IN">
      <x> 1064.00 </x>
      <y>  140.00 </y>
      <z> -58.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>8</feed>
    <feed>9</feed>
    <feed>12</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> 1064.00 </x>
      <y>  140.00 </y>
      <z> -58.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
  <!-- Fuel System

  Tank  Name   Engine  Capacity (lbs)
  0     Port1  0        5040
  1     Port2  1        7600
  2     Port3  1        5040
  3     Port4  0        5040
  4     Port5  0        4104
  5     Port6  1        5896
  6     Port7  0        4400

  -->

  <tank type="FUEL" number="0">
    <!-- Port #1, feeding engine 0 -->
     <location unit="IN">
       <x> 259.38 </x>
       <y> -50.00 </y>
       <z> -29.97 </z>
     </location>
     <capacity unit="LBS"> 5040.0 </capacity>
     <contents unit="LBS"> 5000.0 </contents>
     <priority>1</priority>
  </tank>

  <tank type="FUEL" number="1">
    <!-- Port #2, feeding engine 1 -->
     <location unit="IN">
       <x> 300.38 </x>
       <y> -50.00 </y>
       <z> -29.97 </z>
     </location>
     <capacity unit="LBS"> 7600.0 </capacity>
     <contents unit="LBS"> 7600.0 </contents>
     <priority>1</priority>
  </tank>

  <tank type="FUEL" number="2">
     <!-- Port #3, feeding engine 1 -->
     <location unit="IN">
       <x> 659.38 </x>
       <y> -160.00 </y>
       <z> -29.97 </z>
     </location>
     <capacity unit="LBS"> 5040.0 </capacity>
     <contents unit="LBS"> 5040.0 </contents>
     <priority>2</priority>
  </tank>

  <tank type="FUEL" number="3">
    <!-- Port #4, feeding engine 0 -->
     <location unit="IN">
       <x> 720.38 </x>
       <y> -160.00 </y>
       <z> -29.97 </z>
     </location>
     <capacity unit="LBS"> 5040.0 </capacity>
     <contents unit="LBS"> 5040.0 </contents>
     <priority>3</priority>
  </tank>

  <tank type="FUEL" number="4">
    <!-- Port #5, feeding engine 0 -->
    <location unit="IN">
      <x> 720.38 </x>
      <y> -200.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 4104.0 </capacity>
    <contents unit="LBS"> 4104.0 </contents>
    <priority>4</priority>
  </tank>

  <tank type="FUEL" number="5">
    <!-- Port #6, feeding engine 1 -->
    <location unit="IN">
      <x> 759.38 </x>
      <y>-160.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 5896.0 </capacity>
    <contents unit="LBS"> 5896.0 </contents>
    <priority>2</priority>
  </tank>  

  <tank type="FUEL" number="6">
    <!-- Port #7, feeding engine 0 -->
    <location unit="IN">
      <x> 759.38 </x>
      <y>-200.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 4400.0 </capacity>
    <contents unit="LBS"> 4400.0 </contents>
    <priority>5</priority>
  </tank>


  <tank type="FUEL" number="7">
    <!-- Starboard #1, feeding engine 3 -->
    <location unit="IN">
      <x> 259.38 </x>
      <y>  50.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 5040.0 </capacity>
    <contents unit="LBS"> 5000.0 </contents>
    <priority>1</priority>
  </tank>
  
  <tank type="FUEL" number="8">
    <!-- Starboard #2, feeding engine 2 -->
    <location unit="IN">
      <x> 300.38 </x>
      <y>  50.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 7600.0 </capacity>
    <contents unit="LBS"> 7600.0 </contents>
    <priority>1</priority>
  </tank>
  
  <tank type="FUEL" number="9">
    <!-- Starboard #3, feeding engine 2 -->
    <location unit="IN">
      <x> 659.38 </x>
      <y>  160.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 5040.0 </capacity>
    <contents unit="LBS"> 5040.0 </contents>
    <priority>2</priority>
  </tank>
  
  <tank type="FUEL" number="10">
    <!-- Starboard #4, feeding engine 3 -->
    <location unit="IN">
      <x> 720.38 </x>
      <y>  160.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 5040.0 </capacity>
    <contents unit="LBS"> 5040.0 </contents>
    <priority>2</priority>
  </tank>
  
  <tank type="FUEL" number="11">
    <!-- Starboard #5, feeding engine 3 -->
    <location unit="IN">
      <x> 720.38 </x>
      <y>  200.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 4104.0 </capacity>
    <contents unit="LBS"> 4104.0 </contents>
    <priority>3</priority>
  </tank>
  
  <tank type="FUEL" number="12">
    <!-- Starboard #6, feeding engine 2 -->
    <location unit="IN">
      <x> 759.38 </x>
      <y> 160.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 5896.0 </capacity>
    <contents unit="LBS"> 5896.0 </contents>
    <priority>3</priority>
  </tank>
  
  <tank type="FUEL" number="13">
    <!-- Starboard #7, feeding engine 3 -->
    <location unit="IN">
      <x> 759.38 </x>
      <y> 200.00 </y>
      <z> -29.97 </z>
    </location>
    <capacity unit="LBS"> 4400.0 </capacity>
    <contents unit="LBS"> 4400.0 </contents>
    <priority>4</priority>
  </tank>
    
 </propulsion>
 
 <system file="pushback"/> 

 <flight_control name="FCS: Vulcan B2">

  <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>  0.30 </max>
      </range>
      <output>fcs/elevator-pos-rad</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>

  </channel>

<channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <limit>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </limit>
   </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>
      <limit>
        <min> -0.1 </min>
        <max>  0.1 </max>
      </limit>
   </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>
      <limit>
        <min> -1 </min>
        <max>  1 </max>
      </limit>
   </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>

  </channel>
  
<!-- No flaps on the Vulcan 
  <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>

  </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/spoiler-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 0.5 </position>
          <time>     5 </time>
       </setting>
       <setting>
          <position> 1.0 </position>
          <time>     3 </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> 0.00000 </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> 0.00183 </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>0.05</value>
         </product>
    </function>

    <function name="aero/coefficient/CDbc">
       <description>Drag_due_to_braking_chute</description>
         <product>
           <property>aero/qbar-psf</property>
           <!-- <property>metrics/Sw-sqft</property> -->
           <property>/controls/chute-pos-norm</property>
           <value>5000.0</value> <!-- a complete guess -->
         </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>
 
 <external_reactions>
	 <force name="pushback" frame="BODY">
		<location unit="IN">
		 <x>  -139 </x>
		 <y>    0.0 </y>
		 <z>  -71.0 </z>
		</location>
		<direction>
		 <x>1</x>
		 <y>0</y>
		 <z>0</z>
		</direction>
	 </force>
 </external_reactions>
 
</fdm_config>