CessnaTD337-JSB.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Cessna _337" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">



<!--
  File:     Cessna _337.xml
  Inputs:
    name:          Cessna _337
    type:          light single
    max weight:    4500.405 lb
    wing span:     37.99398 ft
    length:        29.75867 ft
    wing area:     201.3055 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   piston
    engine layout: middle fuselage
    yaw damper?    no

  Outputs:
    wing loading:  22.36 lb/sq-ft
    CL-alpha:      5 per radian
    CL-0:          0.25
    CL-max:        1.4
    CD-0:          0.024
    K:             0.04
-->

              <!-- Medidas y pesos -->
 <metrics>
   <wingarea  unit="FT2">  201.31 </wingarea>
   <wingspan  unit="FT" >   37.99 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >    5.30 </chord>
   <htailarea unit="FT2">   32.21 </htailarea>
   <htailarm  unit="FT" >   15.47 </htailarm>
   <vtailarea unit="FT2">   20.13 </vtailarea>
   <vtailarm  unit="FT" >   14.88 </vtailarm>
   <location name="AERORP" unit="M">
     <x> 0.391881</x> <!-- <x> 0.583126</x> -->    
     <y> 0.00    </y>
     <z>-0.125318</z>          
   </location>
   <location name="EYEPOINT" unit="M">
     <x>-0.373067</x>
     <y>-0.27    </y>
     <z> 0.357481</z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">      2206 </ixx>
   <iyy unit="SLUG*FT2">      2406 </iyy>
   <izz unit="SLUG*FT2">      4244 </izz>
   <emptywt unit="LBS" >      2700 </emptywt>
   <location name="CG" unit="M">
     <x> 0.391881</x>
     <y> 0.00    </y>
     <z>-0.125318</z>
   </location> 
   
	<pointmass name="Pilot">
		<weight unit="LBS"> 180.0 </weight>
		<location name="POINTMASS" unit="M">
			<x>-0.290</x>
			<y>-0.280</y>
			<z>-0.292</z>
		</location>
	</pointmass>

	<pointmass name="Passenger 1">
		<weight unit="LBS"> 0 </weight>
		<location name="POINTMASS" unit="M">
			<x>-0.290</x>
			<y> 0.280</y>
			<z>-0.292</z>
		</location>
	</pointmass>
	
	<pointmass name="Passenger 2">
		<weight unit="LBS"> 0 </weight>
		<location name="POINTMASS" unit="M">
			<x> 0.440</x>
			<y>-0.280</y>
			<z>-0.292</z>
		</location>
	</pointmass>
	
	<pointmass name="Passenger 3">
		<weight unit="LBS"> 0 </weight>
		<location name="POINTMASS" unit="M">
			<x> 0.440</x>
			<y> 0.280</y>
			<z>-0.292</z>
		</location>
	</pointmass>

	<pointmass name="Passenger 4">
		<weight unit="LBS"> 0 </weight>
		<location name="POINTMASS" unit="M">
			<x> 1.170</x>
			<y>-0.280</y>
			<z>-0.292</z>
		</location>
	</pointmass>

	<pointmass name="Passenger 5">
		<weight unit="LBS"> 0 </weight>
		<location name="POINTMASS" unit="M">
			<x> 1.170</x>
			<y> 0.280</y>
			<z>-0.292</z>
		</location>
	</pointmass> 
 
 </mass_balance>
 
<!-- Tren de aterrizaje -->
 <ground_reactions>

  <contact type="BOGEY" name="NOSE">   
  	<location unit="M">
     <x>-1.60136</x>
     <y> 0.00   </y>
     <z>-1.35708</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">       3450.12 </spring_coeff>    
   <damping_coeff unit="LBS/FT/SEC">   2550.04 </damping_coeff>   
   <max_steer unit="DEG">40</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="M">
     <x> 0.803253</x>
     <y>-1.34673 </y>
     <z>-1.33294 </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">       4500.40 </spring_coeff>   
   <damping_coeff unit="LBS/FT/SEC">   900.08 </damping_coeff>  
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="M">
     <x> 0.803253</x>
     <y> 1.34673 </y>
     <z>-1.33294 </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">       4500.40 </spring_coeff>  
   <damping_coeff unit="LBS/FT/SEC">   900.08 </damping_coeff>  
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>
 
<!-- Alas -->
  <contact type="STRUCTURE" name="LEFT_WING">    
    <location unit="M">
     <x> 0.387301</x>
     <y>-5.88054 </y>
     <z> 0.80836 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4500.40 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   900.08 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">    
    <location unit="M">
     <x> 0.387301</x>
     <y> 5.88054 </y>
     <z> 0.80836 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4500.40 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   900.08 </damping_coeff>
 </contact>

<!-- Patin de cola -->
  <contact type="STRUCTURE" name="TAIL_SKID">    
    <location unit="M">
     <x> 5.20673 </x>
     <y> 0.00    </y>
     <z>-0.076245</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      18500.40 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   600.08 </damping_coeff>
 </contact>

 <!-- Nariz -->
  <contact type="STRUCTURE" name="NOSE">    
    <location unit="M">
     <x>-2.25711</x>
     <y> 0.0     </y>
     <z>-0.520764</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       8500.40 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  1900.08 </damping_coeff>
 </contact>

<!-- Estabilizador vertical -->
  <contact type="STRUCTURE" name="VERTICAL_TAIL">    
    <location unit="M">
     <x> 5.4689 </x>
     <y> 0.0    </y>
     <z> 1.58905</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4500.40 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   900.08 </damping_coeff>
 </contact>

 <!-- Techo de la cabina -->
  <contact type="STRUCTURE" name="CABIN_TOP">    
    <location unit="M">
     <x>-0.311865</x>
     <y> 0.0     </y>
     <z> 0.654836</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4500.40 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   900.08 </damping_coeff>
 </contact> 

 </ground_reactions>
 
<!-- Motores y helices -->
 <propulsion>
 	
<!-- Delantero -->
<engine file="engine_TD4L">
	<location unit="M">
		<x>-1.85601 </x>
		<y> 0.00    </y>
		<z>-0.069293</z>
	</location>
	<orient unit="DEG">
		<pitch>-3</pitch> 
		<roll>  0</roll> 
		<yaw>   0</yaw> 
	</orient>
	<feed>0</feed>
	<thruster file="prop_IO360C">
		<location unit="M">
			<x>-2.52872</x>
			<y> 0.00 </y>
			<z>-0.089188</z>
		</location>
		<orient unit="DEG">
			<pitch>-3</pitch>
			<roll>  0</roll>
			<yaw>   0</yaw>
		</orient>
		<sense>1</sense>
	</thruster>
</engine> 

<!-- Trasero -->
   <engine file="engine_TD4L">
   	<location unit="M">
      <x>2.31968</x>
      <y> 0.00 </y>
      <z>0.290422</z>
    </location>
    <orient unit="DEG">
      <pitch>0</pitch>
      <roll> 0</roll>
      <yaw>180</yaw>
    </orient>
    <feed>1</feed>
    <thruster file="prop_IO360C">
    <location unit="M">
      <x>2.85175</x>
      <y> 0.00 </y>
      <z>0.298886</z>
    </location>
    <orient unit="DEG">
       <pitch>0</pitch>
       <roll> 0</roll>
       <yaw>  0</yaw>
     </orient>
		<sense>-1</sense>
    </thruster>
  </engine>
  
<!-- Tanques de combustible ** Combustible Avgas peso 6.02 lb por galon -->
<!-- Dos tanques de combustible de 75-galones cada uno -->
	<tank type="FUEL" number="0">
		<location unit="M">
			<x> 0.387413</x>
			<y>-0.973096</y>
			<z> 0.552551</z>
		</location>
		<capacity unit="LBS"> 451.50 </capacity>
		<contents unit="LBS"> 225.00 </contents>
	</tank>

	<tank type="FUEL" number="1">
		<location unit="M">
			<x> 0.387413</x>
			<y> 0.973096</y>
			<z> 0.552551</z>
		</location>
		<capacity unit="LBS"> 451.50 </capacity>
		<contents unit="LBS"> 225.00 </contents>
	</tank>
</propulsion>
 
<!-- *Controles* -->
<flight_control name="FCS: Cessna _337">
 	
<!-- Controles elevacion -->
  <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>
  
<!-- Controles de los alerones -->
  <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>

<!-- Controles del Timon -->
  <channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.45 </min>
        <max>  0.45 </max>
      </clipto>
   </summer>
   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-command-sum</input>
      <range>
        <min> -0.45 </min>
        <max>  0.45 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>
   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.45 </min>
        <max>  0.45 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>
  </channel>

<!-- Controles de los Flaps -->
  <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>

<!-- Controles tren de aterrizaje -->
  <channel name="Landing Gear">
   <kinematic name="Gear Control">
     <input>gear/gear-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     5 </time>
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>
  </channel>
  
  <!-- Aerofrenos  -->
  <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>

   <!-- Cowl Flaps --> 
  <channel name="Cowl Flaps">
   <kinematic name="Front Cowl Flaps">
     <input>/controls/engines/engine[0]/cowl-flaps-norm</input>
     <traverse>
       <setting>
          <position>0</position>
          <time>0</time>
       </setting>
       <setting>
          <position>1</position>
          <time>1</time>
       </setting>
     </traverse>
     <output>propulsion/engine[0]/cowl-flaps-norm</output>
   </kinematic>
   <aerosurface_scale name="Front Cooling Factor"> 
     <input>propulsion/engine[0]/cowl-flaps-norm</input>
     <gain>1.0</gain>
     <zero_centered>false</zero_centered>
       <domain>
          <min>0</min>
          <max>1</max>
       </domain>
       <range>
          <min>0.48</min>
          <max>0.75</max>
       </range>
     <output>propulsion/engine[0]/cooling-factor</output>
     </aerosurface_scale>
     
   <kinematic name="Rear Cowl Flaps"> 
     <input>/controls/engines/engine[1]/cowl-flaps-norm</input>
     <traverse>
       <setting>
          <position>0</position>
          <time>0</time>
       </setting>
       <setting>
          <position>1</position>
          <time>1</time>
       </setting>
     </traverse>
     <output>propulsion/engine[1]/cowl-flaps-norm</output>
   </kinematic>
   <aerosurface_scale name="Rear Cooling Factor"> 
     <input>propulsion/engine[1]/cowl-flaps-norm</input>
     <gain>1.0</gain>
     <zero_centered>false</zero_centered>
       <domain>
          <min>0</min>
          <max>1</max>
       </domain>
       <range>
          <min>0.48</min>
          <max>0.75</max>
       </range>
     <output>propulsion/engine[1]/cooling-factor</output>
     </aerosurface_scale>
  </channel>

 </flight_control>

<!-- *Aerodinamica* -->
 <aerodynamics>

<!-- Sustentacion -->
  <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 -0.750
               0.00 0.250
             0.23    1.400
               0.60 0.710
            </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> 0.01333 </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>

<!-- Resistencia al avance -->
  <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    0.031
              0.00    0.024
              0.26    0.031
              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>0.04</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/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> 0.00100 </value>
         </product>
    </function>

    <function name="aero/coefficient/CDgear">
       <description>Drag_due_to_gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.03</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>0.024</value>
         </product>
    </function>

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

    <function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.04</value>
       </product>
    </function>

  </axis>

<!-- Lateral -->
  <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>

<!-- Momentos -->
  <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    0.170
              2.0    0.057
            </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>

<!-- Momentos -->
  <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>-0.5</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     -1.100
              2.0     -0.275
            </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>-12</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>-7</value>
       </product>
    </function>

  </axis>

<!-- Momentos -->
  <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>0.15</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>-1.80</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>-0.01</value>
       </product>
    </function>

  </axis>

</aerodynamics>

<system file="crash-detect"/>

</fdm_config>