<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="ZivkoEdge540" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author>Torsten Dreyer</author>
  <filecreationdate> 2008-02-06 </filecreationdate>
  <version>$Revison: $</version>
  <description>Zivko Edge 540 aerobatic plane</description>
 </fileheader>

 <metrics>
   <wingarea  unit="FT2">   98.00 </wingarea>
   <wingspan  unit="FT" >   24.30 </wingspan>
   <wing_incidence>          0.00 </wing_incidence>
   <chord     unit="FT" >    4.03 </chord>
   <htailarea unit="FT2">   15.68 </htailarea>
   <htailarm  unit="FT" >   10.66 </htailarm>
   <vtailarea unit="FT2">    9.80 </vtailarea>
   <vtailarm  unit="FT" >   10.25 </vtailarm>
   <location name="AERORP" unit="IN">
     <x>13.4 </x>
     <y>0.00</y>
     <z>47.6</z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>56.3</x>
     <y>0.0</y>
     <z>65.3</z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">       361 </ixx>
   <iyy unit="SLUG*FT2">       457 </iyy>
   <izz unit="SLUG*FT2">       742 </izz>
   <emptywt unit="LBS" >      1080 </emptywt>
   <location name="CG" unit="IN">
     <x>13.4</x>
     <y>0.00</y>
     <z>47.6</z>
   </location>
 </mass_balance>

<!--
  x points towards back
  y points towards right
  z points up
-->
 <ground_reactions>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>0</x>
     <y>-32.8</y>
     <z>0</z>
   </location>
   <static_friction>  0.95 </static_friction>
   <dynamic_friction> 0.80 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       2500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x>0</x>
     <y>32.8</y>
     <z>0</z>
   </location>
   <static_friction>  0.95 </static_friction>
   <dynamic_friction> 0.80 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       2500.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="BOGEY" name="TAIL">
   <location unit="IN">
     <x> 171.5 </x>
     <y>   0.00 </y>
     <z> 27.5 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.70 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       800.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  040.00 </damping_coeff>
   <max_steer unit="DEG"> -15.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="STRUCTURE" name="NOSE">
    <location unit="IN">
     <x>-54.1 </x>
     <y>0</y>
     <z>46.7</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1800.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x>19.1</x>
     <y>-146</y>
     <z>48.1 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1800.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x>19.1</x>
     <y>146</y>
     <z>48.1</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1800.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="TAIL">
    <location unit="IN">
     <x>166</x>
     <y>0</y>
     <z>100</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       1800.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   360.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="io540">
    <location unit="IN">
      <x>-20.0</x>
      <y>0.0</y>
      <z>46.5</z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <thruster file="prop">
     <location unit="IN">
       <x>-41.8</x>
       <y>0</y>
       <z>46.5</z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <!-- right wing 79ltr-->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x>25.6</x>
       <y>46.0</y>
       <z>48.0</z>
     </location>
     <density unit="LBS/GAL"> 6.02 </density> <!-- Avgas -->
     <capacity unit="LBS">125.0</capacity>
     <contents unit="LBS">2.0</contents>
  </tank>

  <!-- left wing 79ltr-->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x>25.6</x>
       <y>-46.0</y>
       <z>48.0</z>
     </location>
     <density unit="LBS/GAL"> 6.02 </density> <!-- Avgas -->
     <capacity unit="LBS">125.0</capacity>
     <contents unit="LBS">2.0</contents>
  </tank>

  <!-- fuselage 71ltr-->
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x>10</x>
       <y>0</y>
       <z>45.0</z>
     </location>
     <density unit="LBS/GAL"> 6.02 </density> <!-- Avgas -->
     <capacity unit="LBS">112.0</capacity>
     <contents unit="LBS">112.0</contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: ZivkoEdge540">

  <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>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-command-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>

 </flight_control>

 <aerodynamics>
   <function name="aero/function/cos-alpha">
    <description>Cosine of alpha</description>
     <cos>
      <property>aero/alpha-rad</property>
     </cos>
   </function>

   <function name="aero/function/sin-alpha">
    <description>Sine of alpha</description>
     <sin>
      <property>aero/alpha-rad</property>
     </sin>
   </function>

   <function name="aero/function/cos-beta">
    <description>Cosine of beta</description>
     <cos>
      <property>aero/beta-rad</property>
     </cos>
   </function>
 
   <function name="aero/function/sin-beta">
    <description>Sine of beta</description>
     <sin>
      <property>aero/beta-rad</property>
     </sin>
   </function>

   <function name="aero/function/cos2-alpha">
    <description>Cosine Squared of alpha</description>
     <product>
      <property>aero/function/cos-alpha</property>
      <property>aero/function/cos-alpha</property>
     </product>
   </function>

   <function name="aero/function/scos2-alpha">
    <description>Signed Cosine Squared of alpha</description>
     <product>
      <abs><property>aero/function/cos-alpha</property></abs>
      <property>aero/function/cos-alpha</property>
     </product>
   </function> 

  <function name="aero/function/velocity-induced-fps">
   <description> velocity including the propulsion induced velocity.</description>
   <sum>
    <property>velocities/u-aero-fps</property>
    <property>propulsion/engine/prop-induced-velocity_fps</property>
    <property>propulsion/engine/prop-induced-velocity_fps</property>
   </sum>
  </function> 

  <function name="aero/function/qbar-induced-psf">
   <description> q bar including the propulsion induced velocity.</description>
   <product>
    <property>aero/function/velocity-induced-fps</property>
    <property>aero/function/velocity-induced-fps</property>
    <property>atmosphere/rho-slugs_ft3</property>
    <value>0.5</value>
   </product>
  </function> 

  <function name="aero/function/kCDge">
    <description>Change_in_drag_due_to_ground_effect</description>
    <product>
      <table>
        <independentVar>aero/h_b-mac-ft</independentVar>
        <tableData>
          0.0000	0.4800
          0.1000	0.5150
          0.1500	0.6290
          0.2000	0.7090
          0.3000	0.8150
          0.4000	0.8820
          0.5000	0.9280
          0.6000	0.9620
          0.7000	0.9880
          0.8000	1.0000
          0.9000	1.0000
          1.0000	1.0000
          1.1000	1.0000
       </tableData>
      </table>
    </product>
  </function>

  <function name="aero/function/kCLge">
    <description>Change_in_lift_due_to_ground_effect</description>
    <product>
      <table>
        <independentVar>aero/h_b-mac-ft</independentVar>
        <tableData>
           0.0000	1.2030
           0.1000	1.1270
           0.1500	1.0900
           0.2000	1.0730
           0.3000	1.0460
           0.4000	1.0350
           0.5000	1.0190
           0.6000	1.0130
           0.7000	1.0080
           0.8000	1.0060
           0.9000	1.0030
           1.0000	1.0020
           1.1000	1.0000
        </tableData>
      </table>
    </product>
  </function>

  <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>
          <property>aero/function/kCLge</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -3.14  0.05
              -2.36  1.0
              -1.57  0
              -0.78  1.0
              -0.60  0.7
              -0.28 -1.12
              -0.25 -1.34
              -0.22 -1.40
              -0.20 -1.34
               0.00  0.00
               0.20  1.34
               0.22  1.40
               0.25  1.34
               0.28  1.12
               0.60  0.7
               0.78  1.0
               1.57  0.0
               2.36 -1.0
               3.14  0.05
            </tableData>
          </table>
      </product>
    </function>
<!--
    <function name="aero/coefficient/CLde">
       <description>Lift_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-rad</property>
           <property>aero/function/cos-alpha</property>
           <value>0.0</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>
             -3.142   0.06
             -1.57    1.500
             -0.26    0.036
              0.00    0.028
              0.26    0.036
              1.57    1.500
              3.142   0.06
            </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>0.04</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
                0.7       0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </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>
              -3.142  0.006
              -1.57   1.930
              -0.26   0.250
               0.00    0.000
               0.26    0.250
               1.57    1.930
               3.142   0.006
            </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>
           <property>aero/cl-squared</property>
           <property>fcs/mag-elevator-pos-rad</property>
           <property>aero/function/cos2-alpha</property>
           <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/function/sin-beta</property>
           <value>-2.2</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/function/sin-beta</property>
           <value>-0.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Clp">
       <description>Roll moment due to roll rate extended to work at zero velocity</description>
       <product>
        <value>-0.4</value> <!-- Clp -->
        <property>velocities/p-aero-rad_sec</property>
        <property>atmosphere/rho-slugs_ft3</property>
        <property>metrics/Sw-sqft</property>
        <property>metrics/bw-ft</property>
        <property>metrics/bw-ft</property> <!-- b^2 -->
        <value>0.0625</value> <!-- constant from function -->
        <pow>
         <sum>
          <product>
           <property>metrics/bw-ft</property>
           <property>metrics/bw-ft</property> <!-- b^2 -->
           <property>velocities/p-aero-rad_sec</property>
           <property>velocities/p-aero-rad_sec</property><!-- Omega^2 -->
          </product>
          <product>
           <property>velocities/u-aero-fps</property>
           <property>velocities/u-aero-fps</property>
           <value>16</value>
          </product>
         </sum>
         <value>0.5</value>
        </pow>
       </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>
          <value>0.28</value>
          <property>aero/function/cos-alpha</property>
       </product>
    </function>

    <function name="aero/coefficient/Cldr">
       <description>Roll_moment_due_to_rudder</description>
       <product>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>0.0035</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/function/sin-alpha</property>
           <value>-1.2</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmde">
       <description>Pitch_moment_due_to_elevator</description>
       <product>
          <property>aero/function/qbar-induced-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <value>-1.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmq">
       <description>Pitch_moment_due_to_pitch_rate extended to work at zero velocity</description>
       <product>
        <value>-1.446</value> <!-- CMAD -->
        <property>velocities/q-aero-rad_sec</property>
        <property>atmosphere/rho-slugs_ft3</property>
        <property>metrics/Sw-sqft</property>
        <property>metrics/cbarw-ft</property>
        <property>metrics/cbarw-ft</property> <!-- b^2 -->
        <value>0.0625</value> <!-- constant from function -->
        <pow>
         <sum>
          <product>
           <property>metrics/cbarw-ft</property>
           <property>metrics/cbarw-ft</property> <!-- b^2 -->
           <property>velocities/q-aero-rad_sec</property>
           <property>velocities/q-aero-rad_sec</property><!-- Omega^2 -->
          </product>
          <product>
           <property>velocities/u-aero-fps</property>
           <property>velocities/u-aero-fps</property>
           <value>16</value>
          </product>
         </sum>
         <value>0.5</value>
        </pow>
       </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>-7</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/function/sin-beta</property>
           <value>0.12</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnr">
       <description>Yaw_moment_due_to_yaw_rate extended to work at zero velocity</description>
       <product>
        <value>-0.1411</value> <!-- CNR -->
        <property>velocities/r-aero-rad_sec</property>
        <property>atmosphere/rho-slugs_ft3</property>
        <property>metrics/Sw-sqft</property>
        <property>metrics/bw-ft</property>
        <property>metrics/bw-ft</property> <!-- b^2 -->
        <value>0.0625</value> <!-- constant from function -->
        <pow>
         <sum>
          <product>
           <property>metrics/bw-ft</property>
           <property>metrics/bw-ft</property> <!-- b^2 -->
           <property>velocities/r-aero-rad_sec</property>
           <property>velocities/r-aero-rad_sec</property><!-- Omega^2 -->
          </product>
          <product>
           <property>velocities/u-aero-fps</property>
           <property>velocities/u-aero-fps</property>
           <value>16</value>
          </product>
         </sum>
         <value>0.5</value>
        </pow>
       </product>
      </function>

    <function name="aero/coefficient/Cndr">
       <description>Yaw_moment_due_to_rudder</description>
       <product>
           <property>aero/function/cos-alpha</property>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.035</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnda">
       <description>Adverse_yaw</description>
       <product>
           <property>aero/function/cos-alpha</property>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/left-aileron-pos-rad</property>
           <value>-0.01</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>

