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

 <fileheader>
  <author> BARANGER / DELRUE / Aeromatic v 0.9 </author>
  <filecreationdate> 16 Décembre 2006 </filecreationdate>
  <version> 0.65 </version>
  <description> Hughes H4 Hercules </description>
 </fileheader>

<!--
  Fichier             : Hercules-H4.xml
  Données:
    nom               : hughes H4 Hercules
    type              : transport de troupe
    Poids max.        : 400000 lb					soit  181436.948 kg
    envergure         : 320 ft						soit	  97.536 m
    longueur          : 218.6 ft					soit      66.446 m
    surface ailaire   : 11430 ft2					soit    3483.864 m2
    Type              : hydravion
    Nombre de moteurs : 8
    Moteur            : à pistons
    Place des moteurs : sur les ailes

  Outputs:
    wing loading:  46.37 lb/sq-ft
    CL-alpha:      4.9 par radian
    CL-0:          0.24
    CL-max:        1.4
    CD-0:          0.028
    K:             0.039

    Nous reprenons l'emsemble des résultats de calcul Aeromatic, sans aucune modification de l'essentiel
    (sauf la charge à vide  bien que ...   cela ne soit pas probablement exact).

    nous repositionnons le centre de poussée Aero <location name="AERORP" unit="IN">
    et le centre de gravité   <location name="CG" unit="IN">
    en fonction de la position du modele sur le dessin nous recalculons les valeurs de position des points de contact
    trains virtuels des moteurs et des helices en fonction de la position du modele sur le dessin
-->

 <metrics>
   <wingarea  unit="FT2"> 11430.00 </wingarea>			<!-- Surface ailaire -->
   <wingspan  unit="FT" >   320.00 </wingspan>			<!-- Envergure       -->	
   <wing_incidence>           2.00 </wing_incidence>
   <chord     unit="FT" >    35.72 </chord>
   <htailarea unit="FT2">  1828.80 </htailarea>
   <htailarm  unit="FT" >   109.00 </htailarm>
   <vtailarea unit="FT2">  2057.40 </vtailarea>
   <vtailarm  unit="FT" >   109.00 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> -104.000 </x>						<!---2.650 m sur dessin        Aeromatic 1380 -->
     <y>    0.000 </y>	
     <z>  216.000 </z>						<!--5.15 m sur desin   Aeromatic 0 -->
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 209.280 </x>
     <y> -24.000 </y>
     <z>  65.000 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>   0.000 </x>
     <y>   0.000 </y>
     <z> 106.300 </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">  25888755 </ixx>
   <iyy unit="SLUG*FT2">  14373427 </iyy>
   <izz unit="SLUG*FT2">  39464948 </izz>
   <emptywt unit="LBS" >    400000 </emptywt>  			<!--Aero 318000 -->
   <location name="CG" unit="IN">				<!-- Centre de gravité -->
     <x> -104.000 </x>						<!-- -2.650  m                    Aeromatic 1380 -->
     <y>    0.000 </y>
     <z>  106.300 </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> -708.000 </x>
     <y>    0.000 </y>
     <z>  -20.000 </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">      159000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 53000.00 </damping_coeff>
   <max_steer unit="DEG"> 5.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>FIXED</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>   20.000 </x>
     <y> -422.400 </y>
     <z>  -10.000 </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">      530000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 106000.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>FIXED</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x>  20.000 </x>
     <y> 422.400 </y>
     <z> -10.000 </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">      530000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 106000.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>FIXED</retractable>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x>     0.000 </x>
     <y> -1060.000 </y>
     <z>    65.400 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      530000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 106000.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x>    0.000 </x>
     <y> 1060.000 </y>
     <z>   65.400 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      530000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 106000.00 </damping_coeff>
 </contact>



<!-- ********************************************************************* -->

 </ground_reactions>
    <propulsion>
      <engine file="R4360-Wasp-Major">	<!-- Moteur 1 extérieur droit -->
        <location unit="IN">
          <x> -18.884 </x>		<!-- -5.756 m-->
          <y>  85.814 </y>		<!-- 26.156 m-->
          <z>  22.773 </z>		<!--  6.773 m-->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>0</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -18.884 </x>
            <y>  85.814 </y> 
            <z>  22.773 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> 1 </sens>
	</thruster>
      </engine>
      
      <engine file="R4360-Wasp-Major">	<!-- Moteur 2 extérieur droit interne -->
        <location unit="IN">
          <x> -22.299 </x>		<!-- -6.797 -->
          <y>  65.433 </y>		<!-- 19.944 -->
          <z>  21.125 </z>		<!--  6.439 -->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>1</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -22.299 </x> 
            <y>  65.433 </y>
            <z>  21.125 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch> 
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> -1 </sens>
        </thruster>
      </engine>

      <engine file="R4360-Wasp-Major">	<!-- Moteur 3 interieur droit externe-->
        <location unit="IN">
          <x> -24.275 </x>		<!-- -7.399 -->
          <y>  45.229 </y>		<!-- 13.786 -->
          <z>  19.372 </z>		<!--  5.906 -->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>2</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -24.275 </x>
            <y>  45.229 </y>
            <z>  19.372 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> 1 </sens>
        </thruster>
      </engine>

      <engine file="R4360-Wasp-Major">	<!-- Moteur 4 intérieur droit -->
        <location unit="IN">
          <x> -26.174 </x>		<!-- -7.978 -->
          <y>  24.714 </y>		<!--  7.533 -->
          <z>  17.785 </z>		<!--  4.421 -->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>3</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -26.174 </x>
            <y>  24.714 </y>
            <z>  17.785 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> -1 </sens>
        </thruster>
      </engine>

      <engine file="R4360-Wasp-Major">	<!-- Moteur 5 intérieur gauche -->
        <location unit="IN">
          <x> -26.174 </x>		<!-- -7.978 -->
          <y> -24.714 </y>		<!-- -7.533 -->
          <z>  17.785 </z>		<!--  5.421 -->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>4</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -26.174 </x>
            <y> -24.714 </y>
            <z>  17.785 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> 1 </sens>
        </thruster>
      </engine>

      <engine file="R4360-Wasp-Major"> <!-- Moteur 6 inérieur gauche externe-->
        <location unit="IN">
          <x> -24.275 </x>		<!--  -7.399 -->
          <y> -45.229 </y>		<!-- -13.786 -->
          <z>  19.372 </z>		<!--   5.906 -->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>5</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -24.275 </x>
            <y> -45.229 </y>
            <z>  19.372 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> -1 </sens>
        </thruster>
      </engine>

      <engine file="R4360-Wasp-Major">	<!-- Moteur 7 extérieur gauche interne -->
        <location unit="IN">
          <x> -22.299 </x>		<!--  -6.797 -->
          <y> -65.433 </y>		<!-- -19.944 -->
          <z>  21.125 </z>		<!--   6.439 -->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>6</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="IN">
            <x> -22.299 </x>
            <y> -65.433 </y>
            <z>  21.125 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> 1 </sens>
        </thruster>
      </engine>

      <engine file="R4360-Wasp-Major"> <!-- Moteur 8 extérieur gauche-->
        <location unit="M">
          <x> -18.884 </x>		<!-- -5.756 m-->
          <y> -85.814 </y>		<!-- 26.156 m-->
          <z>  22.773 </z>		<!--  6.773 m-->
        </location>
        <orient unit="DEG">
          <pitch> 0.00 </pitch>
          <roll>  0.00 </roll>
          <yaw>   0.00 </yaw>
        </orient>
        <feed>7</feed>
        <thruster file="R4360-Wasp-Major-prop">
          <location unit="M">
            <x> -18.884 </x>
            <y> -85.814 </y>
            <z>  22.773 </z>
          </location>
          <orient unit="DEG">
            <pitch> 0.00 </pitch>
            <roll>  0.00 </roll>
            <yaw>   0.00 </yaw>
          </orient>
	  <sens> -1 </sens>
        </thruster>
      </engine>

<!-- ********************************************************************* -->	

  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="3">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="4">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="5">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="6">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="7">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

  <tank type="FUEL" number="8">
     <location unit="IN">
       <x> -104.000 </x>
       <y>    0.000 </y>
       <z>  106.300 </z>
     </location>
     <capacity unit="LBS"> 3271.60 </capacity>
     <contents unit="LBS"> 1635.80 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: H4-Hercules">

  <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="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 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="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>

  <channel name="Flaps">
   <kinematic name="Flaps Control">
     <input>fcs/flap-cmd-norm</input>
     <traverse>
       <setting>
         <position>0</position>
         <time>0</time>
       </setting>
       <setting>
         <position>4</position>
         <time>4</time>
       </setting>
       <setting>
         <position>8</position>
         <time>3</time>
       </setting>
       <setting>
         <position>16</position>
         <time>2</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> 16 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Landing Gear">
  </channel>

  <channel name="Speedbrake">
   <kinematic name="Speedbrake Control">
     <input>fcs/speedbrake-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     1 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-norm</output>
   </kinematic>

  </channel>

 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

    <function name="aero/coefficient/CLalpha">
      <description>Lift_due_to_alpha</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -0.20 -0.740
               0.00 0.240
             0.24    1.400
               0.60 0.704
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/coefficient/dCLflap">
       <description>Delta_Lift_due_to_flaps</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.02000 </value>
       </product>
    </function>

    <function name="aero/coefficient/dCLsb">
       <description>Delta_Lift_due_to_speedbrake</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0</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    0.036
              0.00    0.028
              0.26    0.036
              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>0.039</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/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> 0.00117 </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>0.028</value>
         </product>
    </function>

    <function name="aero/coefficient/CDbeta">
       <description>Drag_due_to_sideslip</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57       1.230
              -0.26    0.050
               0.00       0.000
               0.26    0.050
               1.57       1.230
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-norm</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/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    0.150
              2.0    0.050
            </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>-0.4</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     -1.000
              2.0     -0.250
            </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>-22</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>-8</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>-0.008</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>
