<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="DG-101G" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

  <fileheader>
    <author> Nikolaus Kerner </author>
    <filecreationdate> 2009-03-23 </filecreationdate>
    <version> $Revison: 2013-01-01 $ </version>
    <description>Models a Glaser-Dirks DG-101G standard class glider</description>
    <note> some kind of remarks</note>
    <limitation> ground effects not included</limitation>
    <documentation>
       information regarding the plane 
    </documentation>
  </fileheader>


  <metrics>
    <wingarea       unit="M2"> 11.07  </wingarea>
    <wingspan       unit="M">  15.00  </wingspan>
    <chord          unit="M">   0.774 </chord>
    <wing_incidence unit="">    2     </wing_incidence>
    <htailarea      unit="M2">  0.830 </htailarea>
    <htailarm       unit="M">   3.90  </htailarm>
    <vtailarea      unit="M2">  1.02  </vtailarea>
    <vtailarm       unit="M">   4.00  </vtailarm>
    <location name="AERORP" unit="M">
      <x>-0.210 </x>
      <y> 0 </y>
      <z> 0 </z>
    </location>
    <location name="EYEPOINT" unit="M">
      <x>-0.51 </x>
      <y> 0.00 </y>
      <z> 0.15 </z>
    </location>
    <!-- VRP, the virtual reverence point, typically the nose of the plane 
    if set, all coordinates reported by jsbsim are referenced to that point -->
    <location name="VRP" unit="M">
        <x> 0 </x>
        <y> 0 </y>
        <z> 0 </z>
    </location>
  </metrics>


  <mass_balance>
    <ixx unit="KG*M2">1087</ixx>
    <iyy unit="KG*M2">1340</iyy>
    <izz unit="KG*M2">2368</izz>
    <ixz unit="KG*M2">0</ixz>
    <iyz unit="KG*M2">0</iyz>
    <ixy unit="KG*M2">0</ixy>
    <emptywt unit="KG">230</emptywt>
    <location name="CG" unit="M">
      <x>-0.210</x>   <!-- 2.0 - 2.21 = -0.21 -->
      <y> 0.000</y>
      <z>-0.125</z>
    </location>
    
    <!-- pilot  n=0 -->
    <pointmass name="pilot">
      <weight unit="KG">80</weight>
      <location name="POINTMASS" unit="M">
        <x>-0.610</x>  <!-- 1.6 - 2.21 = -0,61 -->
        <y> 0.000</y>
        <z> 0.000</z>
      </location>
    </pointmass>
    <!-- tank1 right wing n=1 -->
    <pointmass name="tank1">
      <weight unit="KG">0</weight>
      <location name="POINTMASS" unit="M">
        <x>-0.210</x>  <!-- 2.0 - 2.21 = -0.21 -->
        <y> 1.500</y>
        <z> 0.000</z>
      </location>
    </pointmass>
    <!-- tank2 left wing n=2 -->
    <pointmass name="tank2">
      <weight unit="KG">0</weight>
      <location name="POINTMASS" unit="M">
        <x>-0.210</x>  <!-- 2.0 - 2.21 = -0.21 -->
        <y>-1.500</y>
        <z> 0.000</z>
      </location>
    </pointmass>
    <!-- payload used for CG finetuning  n=3 -->
    <pointmass name="balancing">
      <weight unit="KG">20</weight>
      <location name="POINTMASS" unit="M">
        <x> 1.790</x>  <!-- 4.0 - 2.21 = 1.79 -->
        <y> 0.000</y>
        <z> 0.000</z>
      </location>
    </pointmass>
  </mass_balance>


  <ground_reactions>
    
    <!-- wheel contacts to ground -->
    
    <contact type="BOGEY" name="MAIN">
      <location unit="M">
        <x>-0.261 </x>  <!-- 1.949 - 2.21 0 = -0.261 -->
        <y> 0 </y>
        <z> -0.679 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 3500.0 </damping_coeff>
      <max_steer unit="DEG"> 0 </max_steer>
      <brake_group> CENTER </brake_group>
      <retractable> 1 </retractable>
    </contact>
    
    <contact type="BOGEY" name="TAIL">
      <location unit="M">
        <x> 4.12 </x>  <!-- 6.33 - 2.21 = 4.12 --> 
        <y> 0 </y>
        <z> -0.17 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="N/M"> 4500.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 1500.0 </damping_coeff>
      <max_steer unit="DEG"> 0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable> 0 </retractable>
    </contact>
    
    <!-- wheel contacts on the wing tips -->
    
    <contact type="BOGEY" name="LEFT_WING">
      <location unit="M">
        <x>  0.086 </x>  <!-- 2.296 - 2.21 = 0.086 -->
        <y> -7.486 </y>
        <z>  0.403 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="N/M"> 20000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
      <max_steer unit="DEG"> 0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable> 0 </retractable>
    </contact>
    
    <contact type="BOGEY" name="RIGHT_WING">
      <location unit="M">
        <x>  0.086 </x>  <!-- 2.296 - 2.21 = 0.086 -->
        <y>  7.486 </y>
        <z>  0.403 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="N/M"> 20000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
      <max_steer unit="DEG"> 0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable> 0 </retractable>
    </contact>
    
    <!-- all other structure contacts -->
    
    <contact type="STRUCTURE" name="BODY_1"> <!-- at the nose -->
      <location unit="M">
        <x>-2.21 </x>  <!-- 0 - 2.21 = -2.21 -->
        <y> 0.00 </y>
        <z>-0.21 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="BODY_2"> <!-- at the bottom -->
      <location unit="M">
        <x>-0.915 </x>  <!-- 1.295 - 2.21 = -0.915 -->
        <y> 0.000 </y>
        <z>-0.480 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="BODY_3"> <!-- at the canopy -->
      <location unit="M">
        <x>-1.105 </x>  <!-- 1.105 - 2.21 = -1.105 -->
        <y> 0.000 </y>
        <z> 0.273 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="WING_L"> <!-- at the left wing -->
      <location unit="M">
        <x> 0.000 </x>
        <y>-7.486 </y>
        <z> 0.500 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="WING_R"> <!-- at the right wing -->
      <location unit="M">
        <x> 0.000 </x>
        <y> 7.486 </y>
        <z> 0.500 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="RUDDER_1"> <!-- at the bottom of the rudder -->
      <location unit="M">
        <x> 4.79 </x>  <!-- 7 - 2.21 = 4.79 -->
        <y> 0.00 </y>
        <z> 0.02 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="ELEV_1"> <!-- at the right elevator tip -->
      <location unit="M">
        <x> 4.407 </x>  <!-- 6.617 - 2.21 = 4.407 -->
        <y> 1.120 </y>
        <z> 1.200 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
    
    <contact type="STRUCTURE" name="ELEV_2"> <!-- at the left elevator tip -->
      <location unit="M">
        <x> 4.407 </x>  <!-- 6.617 - 2.21 = 4.407 -->
        <y>-1.120 </y>
        <z> 1.200 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <spring_coeff unit="N/M"> 80000.0 </spring_coeff>
      <damping_coeff unit="N/M/SEC"> 4000.0 </damping_coeff>
    </contact>
  </ground_reactions>


  <!-- external forces, for winch start and aerotowing -->
  <external_reactions>
    
    <property>fcs/winch-cmd-norm</property>
    
    <force name="winchx" frame="BODY" >
      <location unit="M">
        <x> -0.41</x>  <!-- 1.8 - 2.21 = -0.41 -->
        <y>  0.00</y>
        <z> -0.50</z>
      </location>
      <direction>
        <x> 1.0</x>
        <y> 0.0</y>
        <z> 0.0</z>
      </direction>
    </force>
    
    <force name="winchy" frame="BODY" >
      <location unit="M">
        <x> -0.41</x>  <!-- 1.8 - 2.21 = -0.41 -->
        <y>  0.00</y>
        <z> -0.50</z>
      </location>
      <direction>
        <x> 0.0</x>
        <y> 1.0</y>
        <z> 0.0</z>
      </direction>
    </force>
    
    <force name="winchz" frame="BODY" >
      <location unit="M">
        <x> -0.41</x>  <!-- 1.8 - 2.21 = -0.41 -->
        <y>  0.00</y>
        <z> -0.50</z>
      </location>
      <direction>
        <x> 0.0</x>
        <y> 0.0</y>
        <z> 1.0</z>
      </direction>
    </force>
    
    
    <property>fcs/dragger-cmd-norm</property>
    
    <force name="dragx" frame="BODY" >
      <location unit="M">
        <x> -2.21</x>  <!-- 0 - 2.21 = -2.21 -->
        <y>  0.00</y>
        <z> -0.50</z>
      </location>
      <direction>
        <x> 1.0</x>
        <y> 0.0</y>
        <z> 0.0</z>
      </direction>
    </force>
    
    <force name="dragy" frame="BODY" >
      <location unit="M">
        <x> -2.21</x>  <!-- 0 - 2.21 = -2.21 -->
        <y>  0.00</y>
        <z> -0.50</z>
      </location>
      <direction>
        <x> 0.0</x>
        <y> 1.0</y>
        <z> 0.0</z>
      </direction>
    </force>
    
    <force name="dragz" frame="BODY" >
      <location unit="M">
        <x> -2.21</x>  <!-- 0 - 2.21 = -2.21 -->
        <y>  0.00</y>
        <z> -0.50</z>
      </location>
      <direction>
        <x> 0.0</x>
        <y> 0.0</y>
        <z> 1.0</z>
      </direction>
    </force>
    
  </external_reactions>


  <propulsion>
  </propulsion>


  <flight_control name="FCS: DG-101G">
    
    <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> -0.52 </min>
          <max>  0.52 </max>
        </range>
        <output>fcs/elevator-pos-rad</output>
      </aerosurface_scale>
      
      <aerosurface_scale name="elevator normalization">
        <input>fcs/elevator-pos-rad</input>
        <domain>
          <min> -0.52 </min>
          <max>  0.52 </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> -1 </min>
          <max>  1 </max>
        </clipto>
      </summer>
      
      <aerosurface_scale name="Rudder Control">
        <input>fcs/rudder-command-sum</input>
        <range>
          <min> -0.52 </min>
          <max>  0.52 </max>
        </range>
        <output>fcs/rudder-pos-rad</output>
      </aerosurface_scale>
      
      <aerosurface_scale name="rudder normalization">
        <input>fcs/rudder-pos-rad</input>
        <domain>
          <min> -0.52 </min>
          <max>  0.52 </max>
        </domain>
        <range>
          <min> -1 </min>
          <max>  1 </max>
        </range>
        <output>fcs/rudder-pos-norm</output>
      </aerosurface_scale>
      
    </channel>
    
    <channel name="Flaps">
    
      <kinematic name="Flaps Control">
        <input>fcs/flap-cmd-norm</input>
        <traverse>
          <setting>
            <position>  0 </position>
            <time>      0 </time>
          </setting>
          <setting>
            <position> 15 </position>
            <time>      4 </time>
          </setting>
          <setting>
            <position> 30 </position>
            <time>      3 </time>
          </setting>
        </traverse>
        <output>fcs/flap-pos-deg</output>
      </kinematic>
      
      <aerosurface_scale name="flap normalization">
        <input>fcs/flap-pos-deg</input>
        <domain>
          <min>  0 </min>
          <max> 30 </max>
        </domain>
        <range>
          <min> 0 </min>
          <max> 1 </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>     0.5 </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>     0.5 </time>
          </setting>
        </traverse>
        <output>fcs/speedbrake-pos-norm</output>
      </kinematic>
      
    </channel>
    
    <channel name="Hook">
    
      <kinematic name="Hook Released">
        <input>fcs/winch-cmd-norm</input>
        <traverse>
          <setting>
            <position> 0 </position>
            <time>     0 </time>
          </setting>
          <setting>
            <position> 1 </position>
            <time>     0.5 </time>
          </setting>
        </traverse>
        <output>fcs/hook-pos-norm</output>
      </kinematic>
      
    </channel>
    
    <channel name="BrakesCombined">
    
      <fcs_function name="Brake Gradient">
        <function>
          <sum>
            <value> -0.25 </value>
            <product>
              <value> 0.5 </value>
              <property>fcs/speedbrake-cmd-norm</property>
            </product>
          </sum>
        </function>
        <clipto>
          <min> 0 </min>
          <max> 0.5 </max>
        </clipto>
        <output>fcs/center-brake-cmd-norm</output>
      </fcs_function>
      
    </channel>
    
    <channel name="BallastDrop">
    
      <!-- function t.b.d. -->
      
    </channel>
    
  </flight_control>


  <aerodynamics>
  
    <axis name="LIFT" unit="LBS">
    
      <function name="aero/coefficient/F_CLalpha">
        <description>XFLR5 - Lift Force due to alpha</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/Cl_alpha">
            <independentVar>aero/alpha-rad</independentVar>
            <tableData>
              -0.191986     -0.59658    
              0             0.462428    
              0.18326       1.44513     
              0.20944       1.45        
              0.244346      1.4         
              0.279253      1           
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCLbeta">
        <description>XFLR5 - delta Lift Force due to beta</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCl_beta">
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -0.244346     0.008         -0.015757     -0.032447     -0.04862      -0.07         
              -0.174533     0.004         -0.00824      -0.016825     -0.025163     -0.036        
              -0.139626     0.003         -0.005314     -0.010653     -0.015535     -0.022        
              -0.10472      0.001         -0.003006     -0.006078     -0.009042     -0.013        
              -0.06981      0.0005        -0.00134      -0.00267      -0.00394      -0.0055       
              -0.0523599    0.00035       -0.00075      -0.001447     -0.002016     -0.0026       
              -0.0349066    0.00055       -0.000346     -0.000105     0.001393      0.006         
              -0.0174533    5e-05         -8.4e-05      -0.000141     -0.000113     0.001         
              0             0             0             0             0             0             
              0.0174533     5e-05         -8.4e-05      -0.000141     -0.000113     0.001         
              0.0349066     0.00055       -0.000346     -0.000105     0.001393      0.006         
              0.0523599     0.00035       -0.00075      -0.001447     -0.002016     -0.0026       
              0.06981       0.0005        -0.00134      -0.00267      -0.00394      -0.0055       
              0.10472       0.001         -0.003006     -0.006078     -0.009042     -0.013        
              0.139626      0.003         -0.005314     -0.010653     -0.015535     -0.022        
              0.174533      0.004         -0.00824      -0.016825     -0.025163     -0.036        
              0.244346      0.008         -0.015757     -0.032447     -0.04862      -0.07         
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCLaileron">
        <description>XFRL5 - delta Lift Force due to aileron deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCl_aileron">
            <independentVar lookup="row">fcs/left-aileron-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            -0.105        -0.12         -0.131141     -0.139216     -0.147        
              -0.75         -0.085        -0.095983     -0.101979     -0.106726     -0.111        
              -0.5          -0.062        -0.067585     -0.07049      -0.072553     -0.074        
              -0.25         -0.035        -0.03666      -0.037448     -0.037791     -0.0375       
              0             0             0             0             0             0             
              0.25          -0.035        -0.03666      -0.037448     -0.037791     -0.0375       
              0.5           -0.062        -0.067585     -0.07049      -0.072553     -0.074        
              0.75          -0.085        -0.096        -0.101979     -0.106726     -0.111        
              1             -0.105        -0.12         -0.131141     -0.139216     -0.147        
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCLelevator">
        <description>XFLR5 - delta Lift Force due to elevator deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCl_elevator">
            <independentVar>fcs/elevator-pos-norm</independentVar>
            <tableData>
              -1            -0.110971   
              -0.75         -0.085436   
              -0.5          -0.058065   
              -0.25         -0.029381   
              0             0           
              0.25          0.029378    
              0.5           0.058094    
              0.75          0.085515    
              1             0.111114    
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCLflap">
        <description>Aeromatic - Delta_Lift_due_to_flaps</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/flap-pos-norm</property>
          <value>0</value>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCLsb">
        <description>Aeromatic - Delta_Lift_due_to_speedbrake</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/speedbrake-pos-norm</property>
          <value>-0.05</value>
        </product>
      </function>
      
    </axis>
    
    
    <axis name="DRAG" unit="LBS">
    
      <function name="aero/coefficient/F_CDalpha">
        <description>XFLR5 - Drag Force due to alpha and speed</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/Cd_alpha">
            <independentVar>aero/alpha-rad</independentVar>
            <tableData>
              -0.191986     0.146542    
              -0.174533     0.0940905   
              -0.15708      0.040548    
              -0.139626     0.0229267   
              -0.122173     0.0139683   
              -0.10472      0.0114568   
              -0.069813     0.009294    
              -0.034907     0.0098432   
              0             0.0125125   
              0.034907      0.0175475   
              0.069813      0.024651    
              0.10472       0.03372     
              0.139626      0.0447178   
              0.15708       0.0523157   
              0.174533      0.0613224   
              0.18326       0.0654293   
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDbeta">
        <description>XFLR5 - delta Drag Force due to beta</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCd_beta">
            <independentVar>aero/beta-rad</independentVar>
            <tableData>
              -0.244346     0.0055666   
              -0.174533     0.0027924   
              -0.139626     0.002244    
              -0.10472      0.0009472   
              -0.06981      0.00044     
              -0.0523599    0.0003878   
              -0.0349066    0.0003334   
              -0.0174533    -4.72e-05   
              0             0           
              0.0174533     -4.72e-05   
              0.0349066     0.000334    
              0.0523599     0.0003878   
              0.06981       0.00044     
              0.10472       0.0009472   
              0.139626      0.002244    
              0.174533      0.0027924   
              0.244346      0.0055666   
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDaileron">
        <description>XFLR5 - delta Drag Force due to aileron deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCd_aileron">
            <independentVar>fcs/left-aileron-pos-norm</independentVar>
            <tableData>
              -1            0.013717    
              -0.75         0.006605    
              -0.5          0.002435    
              -0.25         0.000341    
              0             0           
              0.25          0.000341    
              0.5           0.002435    
              0.75          0.006605    
              1             0.013717    
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDelevator">
        <description>XFLR5 - delta Drag Force due to elevator deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCd_elevator">
            <independentVar lookup="row">fcs/elevator-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            0.004         0.011         0.00981       0.005563      -0.0012       
              -0.75         0.008         0.006809      0.005098      0.00278       -0.003        
              -0.5          0.002         0.002628      0.002192      0.000466      -0.003        
              -0.25         -0.004        -0.00039      0.000575      -0.000479     -0.0025       
              0             0             0             0             0             0             
              0.25          -0.006        -0.00318      0.000305      0.001598      0.002         
              0.5           -0.01         -0.00267      0.001981      0.004212      0.008         
              0.75          -0.01         -0.00011      0.004428      0.007994      0.013         
              1             -0.002        0.003585      0.00865       0.012768      0.02          
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDrudder">
        <description>XFLR5 - delta Drag Force due to rudder deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCD_rudder">
            <independentVar>fcs/rudder-pos-norm</independentVar>
            <tableData>
              -1            0.009144    
              -0.75         0.005569    
              -0.5          0.002396    
              -0.25         0.000641    
              0             0           
              0.25          0.000642    
              0.5           0.002397    
              0.75          0.005584    
              1             0.009144    
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDflap">
        <description>Aeromatic - Drag_due_to_flaps</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/flap-pos-deg</property>
          <value>0</value>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDgear">
        <description>Aeromatic - Drag_due_to_gear</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>gear/gear-pos-norm</property>
          <value>0.012</value>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCDsb">
        <description>Aeromatic - Drag_due_to_speedbrakes</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/speedbrake-pos-norm</property>
          <value>0.01</value>
        </product>
      </function>
      
    </axis>
    
    
    <axis name="SIDE" unit="LBS">
    
      <function name="aero/coefficient/F_CYbeta">
        <description>XFLR5 - delta Side Force due to beta</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/Cy_beta">
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -0.244346     0.091         0.061767      0.057358      0.06688       0.103         
              -0.174533     0.068         0.043921      0.038902      0.04402       0.067         
              -0.139626     0.048         0.034792      0.035247      0.043862      0.069         
              -0.10472      0.041         0.025931      0.021868      0.023987      0.037         
              -0.06981      0.028         0.017287      0.014017      0.014913      0.023         
              -0.0523599    0.017         0.01386       0.015126      0.019452      0.03          
              -0.0349066    -0.06         0.024343      0.088869      0.154024      0.242         
              -0.0174533    -0.001        0.00592       0.012063      0.019165      0.03          
              0             0             0             0             0             0             
              0.0174533     0.001         -0.00592      -0.012063     -0.019165     -0.03         
              0.0349066     0.06          -0.024343     -0.088869     -0.154024     -0.242        
              0.0523599     -0.017        -0.01386      -0.015126     -0.019452     -0.03         
              0.06981       -0.028        -0.017287     -0.014017     -0.014913     -0.023        
              0.10472       -0.041        -0.025931     -0.021868     -0.023987     -0.037        
              0.139626      -0.048        -0.034792     -0.035247     -0.043862     -0.069        
              0.174533      -0.068        -0.043921     -0.038902     -0.04402      -0.067        
              0.244346      -0.091        -0.061767     -0.057358     -0.06688      -0.103        
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCYaileron">
        <description>XFLR5 - delta Side Force due to aileron deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCy_aileron">
            <independentVar lookup="row">fcs/left-aileron-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            -0.011        -0.014        -0.015888     -0.017755     -0.02         
              -0.75         -0.008        -0.010442     -0.011979     -0.013432     -0.015        
              -0.5          -0.0055       -0.006946     -0.008001     -0.008991     -0.0102       
              -0.25         -0.0026       -0.003452     -0.003984     -0.004472     -0.005        
              0             0             0             0             0             0             
              0.25          0.0026        0.003452      0.003984      0.004472      0.005         
              0.5           0.0055        0.006946      0.008001      0.008991      0.0102        
              0.75          0.008         0.010442      0.011979      0.013432      0.015         
              1             0.011         0.014         0.015888      0.017755      0.02          
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/F_dCYrudder">
        <description>XFLR5 - delta Side Force due to rudder deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <table name="aero/coefficient/data/dCy_rudder">
            <independentVar>fcs/rudder-pos-norm</independentVar>
            <tableData>
              -1            -0.068297   
              -0.75         -0.051743   
              -0.5          -0.034901   
              -0.25         -0.0176     
              0             0           
              0.25          0.0176      
              0.5           0.034901    
              0.75          0.051743    
              1             0.068297    
            </tableData>
          </table>
        </product>
      </function>
      
    </axis>
    
    
    <axis name="PITCH" unit="LBS*FT">
    
      <function name="aero/coefficient/M_CMPalpha">
        <description>XFLR5 - Pitch Moment due to alpha</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/cbarw-ft</property>
          <table name="aero/coefficient/data/Cm_alpha">
            <independentVar>aero/alpha-rad</independentVar>
            <tableData>
              -0.191986     0.269574    
              -0.174533     0.24481     
              -0.15708      0.201558    
              -0.139626     0.178682    
              -0.10472      0.143314    
              -0.069813     0.103915    
              -0.034907     0.0570852   
              0             0.0028378   
              0.034907      -0.0581738  
              0.069813      -0.125942   
              0.10472       -0.200179   
              0.139626      -0.280633   
              0.174533      -0.365444   
              0.18326       -0.387584   
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMPbeta">
        <description>XFLR5 - delta Pitch Moment due to beta</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/cbarw-ft</property>
          <table name="aero/coefficient/data/dCm_beta">
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -0.244346     -0.03         0.044576      0.112765      0.180113      0.27          
              -0.174533     -0.06         0.02226       0.0881        0.152785      0.25          
              -0.139626     -0.065        0.013572      0.077939      0.141103      0.23          
              -0.10472      -0.075        0.006622      0.070117      0.132606      0.22          
              -0.06981      -0.085        0.001576      0.064225      0.125906      0.21          
              -0.0523599    -0.089        -0.000221     0.062088      0.123384      0.205         
              -0.0349066    -0.09         -0.001614     0.060727      0.120704      0.21          
              -0.0174533    -0.09         -0.00225      0.059835      0.120908      0.205         
              0             0             0             0             0             0             
              0.0174533     -0.09         -0.00225      0.059835      0.120908      0.205         
              0.0349066     -0.09         -0.001614     0.060727      0.120704      0.21          
              0.0523599     -0.089        -0.000221     0.062088      0.123384      0.205         
              0.06981       -0.085        0.001576      0.064225      0.125906      0.21          
              0.10472       -0.075        0.006622      0.070117      0.132606      0.22          
              0.139626      -0.065        0.013572      0.077939      0.141103      0.23          
              0.174533      -0.06         0.02226       0.0881        0.152785      0.25          
              0.244346      -0.03         0.044576      0.112765      0.180113      0.27          
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMPaileron">
        <description>XFLR5 - delta Pitch Moment due to aileron deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/cbarw-ft</property>
          <table name="aero/coefficient/data/dCm_aileron">
            <independentVar lookup="row">fcs/left-aileron-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            -0.005        0             0.006039      0.013902      0.028         
              -0.75         -0.0045       -0.00082      0.003738      0.009557      0.02          
              -0.5          -0.004        -0.000795     0.002441      0.006199      0.012         
              -0.25         -0.002        -0.000243     0.001493      0.003354      0.006         
              0             0             0             0             0             0             
              0.25          -0.002        -0.000243     0.001493      0.003354      0.006         
              0.5           -0.004        -0.000795     0.002441      0.006199      0.012         
              0.75          -0.0045       -0.00082      0.003738      0.009557      0.02          
              1             -0.005        0             0.006039      0.013902      0.028         
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMPelevator">
        <description>XFLR5 - delta Pitch Moment due to elevator deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/cbarw-ft</property>
          <table name="aero/coefficient/data/dCm_elevator">
            <independentVar lookup="row">fcs/elevator-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            0.51          0.57          0.60028       0.614379      0.62          
              -0.75         0.43          0.440682      0.459924      0.471665      0.472         
              -0.5          0.27          0.297954      0.311751      0.319089      0.32          
              -0.25         0.13          0.148992      0.157519      0.16072       0.16          
              0             0             0             0             0             0             
              0.25          -0.15         -0.155817     -0.157496     -0.160034     -0.16         
              0.5           -0.294        -0.304373     -0.310574     -0.315583     -0.314        
              0.75          -0.43         -0.444674     -0.456649     -0.462962     -0.46         
              1             -0.55         -0.57         -0.591207     -0.5994       -0.59         
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMPrudder">
        <description>XFLR5 - delta Pitch Moment due to rudder deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/cbarw-ft</property>
          <table name="aero/coefficient/data/dCm_rudder">
            <independentVar>fcs/rudder-pos-norm</independentVar>
            <tableData>
              -1            -0.016671   
              -0.75         -0.009653   
              -0.5          -0.00452    
              -0.25         -0.001116   
              0             0           
              0.25          -0.001116   
              0.5           -0.004519   
              0.75          -0.009649   
              1             -0.016671   
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMPq">
        <description>Aeromatic - 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>-9</value>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMPadot">
        <description>Aeromatic - 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>-12</value>
        </product>
      </function>
      
    </axis>
    
    
    <axis name="ROLL" unit="LBS*FT">
    
      <function name="aero/coefficient/M_CMRbeta">
        <description>XFLR5 - Roll Moment due to beta</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/bw-ft</property>
          <table name="aero/coefficient/data/Cr_beta">
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -0.244346     0.017         0.013159      0.011481      0.010645      0.011         
              -0.174533     0.0125        0.00966       0.008378      0.007794      0.008         
              -0.139626     0.0095        0.00779       0.006884      0.006334      0.0062        
              -0.10472      0.0078        0.005878      0.005045      0.004684      0.0049        
              -0.06981      0.0053        0.003937      0.003346      0.003101      0.0033        
              -0.0523599    0.0036        0.003004      0.002641      0.002372      0.0022        
              -0.0349066    -0.004        0.002801      0.004019      0.002314      -0.0045       
              -0.0174533    0.00066       0.00107       0.001061      0.000811      0.0001        
              0             0             0             0             0             0             
              0.0174533     -0.00066      -0.00107      -0.001061     -0.000811     -0.0001       
              0.0349066     0.004         -0.002801     -0.004019     -0.002313     0.0045        
              0.0523599     -0.0036       -0.003004     -0.002641     -0.002372     -0.0022       
              0.06981       -0.0053       -0.003937     -0.003345     -0.003101     -0.0033       
              0.10472       -0.0078       -0.005878     -0.005045     -0.004684     -0.0049       
              0.139626      -0.0095       -0.00779      -0.006884     -0.006334     -0.0062       
              0.174533      -0.0125       -0.009659     -0.008378     -0.007794     -0.008        
              0.244346      -0.017        -0.013159     -0.011481     -0.010645     -0.011        
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMRaileron">
        <description>XFLR5 - Roll Moment due to aileron deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-norm</property>
          <value>0.09</value>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMRrudder">
        <description>XFLR5 - Roll Moment due to rudder deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/bw-ft</property>
          <table name="aero/coefficient/data/dCr_rudder">
            <independentVar lookup="row">fcs/rudder-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            -0.0065       -0.004499     -0.00286      -0.001034     0.0015        
              -0.75         -0.005        -0.003472     -0.002188     -0.000805     0.0011        
              -0.5          -0.0035       -0.002366     -0.001484     -0.000551     0.0008        
              -0.25         -0.0017       -0.001199     -0.00075      -0.00028      0.0004        
              0             0             0             0             0             0             
              0.25          0.0017        0.001199      0.00075       0.00028       -0.0004       
              0.5           0.0035        0.002366      0.001484      0.000551      -0.0008       
              0.75          0.005         0.00347       0.002188      0.000805      -0.0011       
              1             0.0065        0.004499      0.00286       0.001034      -0.0015       
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMRlp">
        <description>Aeromatic - 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/M_dCMRlr">
        <description>Aeromatic - 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>
      
    </axis>
    
    
    <axis name="YAW" unit="LBS*FT">
    
      <function name="aero/coefficient/M_CMYbeta">
        <description>XFLR5 - delta Yaw Moment due to beta</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/bw-ft</property>
          <table name="aero/coefficient/data/Cmy_beta">
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -0.244346     -0.0178       -0.015858     -0.013954     -0.01182      -0.009        
              -0.174533     -0.0135       -0.011453     -0.009582     -0.007568     -0.005        
              -0.139626     -0.0092       -0.009126     -0.008788     -0.008283     -0.0075       
              -0.10472      -0.0084       -0.006829     -0.005419     -0.003936     -0.002        
              -0.06981      -0.0058       -0.004566     -0.003455     -0.002296     -0.0008       
              -0.0523599    -0.0033       -0.003662     -0.003784     -0.003818     -0.00378      
              -0.0349066    0.017         -0.006497     -0.023599     -0.039842     -0.06         
              -0.0174533    0.0007        -0.00158      -0.003186     -0.0047       -0.0065       
              0             0             0             0             0             0             
              0.0174533     -0.0007       0.00158       0.003187      0.004701      0.0065        
              0.0349066     -0.017        0.006497      0.023599      0.039842      0.06          
              0.0523599     0.0033        0.003662      0.003784      0.003818      0.00378       
              0.06981       0.0058        0.004566      0.003455      0.002296      0.0008        
              0.10472       0.0084        0.006829      0.005419      0.003936      0.002         
              0.139626      0.0092        0.009126      0.008788      0.008283      0.0075        
              0.174533      0.0135        0.011453      0.009582      0.007568      0.005         
              0.244346      0.0178        0.015858      0.013954      0.01182       0.009         
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMYaileron">
        <description>XFLR5 - delta Yaw Moment due to aileron deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/bw-ft</property>
          <table name="aero/coefficient/data/dCmy_aileron">
            <independentVar lookup="row">fcs/left-aileron-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            0.00021       0.00018       0.000146      9.9e-05       2e-05         
              -0.75         0.00016       0.000141      0.000114      7.8e-05       1.8e-05       
              -0.5          0.00011       9.7e-05       7.9e-05       5.4e-05       1.2e-05       
              -0.25         5e-05         5e-05         4e-05         2.8e-05       7e-06         
              0             0             0             0             0             0             
              0.25          -5e-05        -5e-05        -4e-05        -2.8e-05      -7e-06        
              0.5           -0.00011      -9.7e-05      -7.9e-05      -5.4e-05      -1.2e-05      
              0.75          -0.00016      -0.000141     -0.000114     -7.8e-05      -1.8e-05      
              1             -0.00021      -0.00018      -0.000146     -9.9e-05      -2e-05        
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMYrudder">
        <description>XFLR5 - delta Yaw Moment due to rudder deflection</description>
        <product>
          <property>metrics/Sw-sqft</property>
          <property>aero/qbar-psf</property>
          <property>metrics/bw-ft</property>
          <table name="aero/coefficient/data/dCmy_rudder">
            <independentVar lookup="row">fcs/rudder-pos-norm</independentVar>
            <independentVar lookup="column">aero/alpha-rad</independentVar>
            <tableData>
                           -0.20944      -0.0872665    0             0.0872665     0.20944       
              -1            0.017         0.018962      0.020132      0.020837      0.0208        
              -0.75         0.0132        0.0146        0.015256      0.015543      0.0153        
              -0.5          0.0091        0.00995       0.010291      0.010393      0.0101        
              -0.25         0.00465       0.005041      0.00519       0.005218      0.00505       
              0             0             0             0             0             0             
              0.25          -0.00465      -0.005041     -0.00519      -0.005218     -0.00505      
              0.5           -0.0091       -0.00995      -0.010291     -0.010393     -0.0101       
              0.75          -0.0132       -0.014614     -0.015256     -0.015543     -0.0153       
              1             -0.017        -0.018962     -0.020132     -0.020837     -0.0208       
            </tableData>
          </table>
        </product>
      </function>
      
      <function name="aero/coefficient/M_dCMYnr">
        <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>
      
    </axis>
    
    
  </aerodynamics>

</fdm_config>
