<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Nord-2502    from Aeromatic" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">




 <fileheader>
  <author> Aeromatic v 0.9 </author>
  <filecreationdate> 09-06-2007 </filecreationdate>
  <version> 0.2 </version>
  <description> Nord 2502 Noratlas </description>
  <documentation>
Specifications (Nord N-2501)
General characteristics

    * Crew: 4-5
    * Capacity: 45 soldiers, 36 paratroopers, 18 patients with medics, or cargo
    * Length: 72 ft 1 in (21.96 m)
    * Wingspan: 106 ft 8 in (32.5 m)
    * Height: 19 ft 8 in (6.0 m)
    * Wing area: 1089 ft² (101.2 m²)
    * Empty weight: 28,825 lb (13,075 kg)
    * Useful load: 18,647 lb (8,458 kg)
    * Max takeoff weight: 48,500 lb (22,000 kg)
    * Powerplant: 2× SNECMA-manufactured Bristol Hercules 738/739 radial engine, 2,040 hp (1,520 kW) each


Performance

    * Maximum speed: 251 mph (405 km/h) under full load
    * Cruise speed: 199 mph (320 km/h) at 1,500 meters
    * Range: 1,550 mi (2,500 km)
    * Service ceiling: 23,300 ft (7,100 m)
    * Rate of climb: 1,080 ft/min (5.5 m/s)

    Empty weight	13300 kg
    Gross weight	21700 kg
    Max speed	405 km/h at 1500 m
    Cruise speed	320 km/h at 1500 m
    Ceiling	7100 m
    Climb	6 m/sec
    Take-off field	810 m
    Landing field	420 m
    Engines	2 SNECMA-Bristol Hercules 738/739/758/759 of 2040 hp each

    Nord 2501D
    Production version for the German Air Force, replaced some systems components of the N2501 with their equivalent from German manufacturers, 186 built (25 French built and 116 German built).

    Nord 2502A
    Civil version for UAT with two Turbomeca Marboré II turbojets and two Bristol Hercules 758/759 turboprops of 1650 hp each, five built and two conversions from N2501A.

    Nord 2504
    Modification of the Nord 2502 intended for antisubmarine warfare role with the French Navy, 24 ordered but only one built.



</documentation>
 </fileheader>


<metrics>
   <wingarea  unit="FT2"> 1087.27 </wingarea>
   <wingspan  unit="FT" >  110.24 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >    12.10 </chord>
   <htailarea unit="FT2">  177 </htailarea>
   <htailarm  unit="FT" >   42</htailarm>
   <vtailarea unit="FT2">  119.47</vtailarea>
   <vtailarm  unit="FT" >   42</vtailarm>

   <location name="AERORP" unit="IN">
     <x> 17.00 </x>
     <y>   0.00 </y>
     <z>   61 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  60.55 </x>
     <y> -32.00 </y>
     <z>  80.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    294010 </ixx>
   <iyy unit="SLUG*FT2">    141906 </iyy>
   <izz unit="SLUG*FT2">    433711 </izz>
   <ixy unit="SLUG*FT2">         0 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >     28900 </emptywt>
   <location name="CG" unit="IN">
     <x> 14.00 </x>
     <y>   0.00 </y>
     <z> -20 </z>
   </location>
    <pointmass name="FRET">
        <weight unit="LBS"> 3000 </weight>
        <location name="POINTMASS" unit="IN">
            <x> 14 </x>
            <y> 0 </y>
            <z> -30 </z>
        </location>
    </pointmass>
 </mass_balance>



 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x>-225.83858 </x>
     <y>   0.00 </y>
     <z>-95.404331 </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">   15214    </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5071 </damping_coeff>
   <max_steer unit="DEG"> 5.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 25.275591</x>
     <y> -153.93504 </y>
     <z> -95.199606 </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">      50715.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 10143.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x> 25.275591</x>
     <y> 153.93504 </y>
     <z> -95.199606 </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">      50715.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 10143.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>
    <contact type="BOGEY" name="W_LEFT">
            <location unit="IN">
            <x> 75.944882 </x>
            <y> -642.63386</y>
            <z> 66.322835 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="W_RIGHT">
            <location unit="IN">
            <x> 75.944882 </x>
            <y> 642.63386</y>
            <z> 66.322835 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="BELLY">
            <location unit="IN">
                <x>-85</x>
                <y> 0 </y>
                <z> -61.968504 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 3000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="NOSE">
            <location unit="IN">
                <x> -264.96063 </x>
                <y> 0 </y>
                <z> 23.599409 </z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="BOGEY" name="TAIL">
            <location unit="IN">
                <x> 495.98819</x>
                <y> 0 </y>
                <z> 6.9980315</z>
            </location>
            <static_friction> 0.2 </static_friction>
            <dynamic_friction> 0.2 </dynamic_friction>
            <rolling_friction> 0.2 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>

 </ground_reactions>

 <propulsion>

   <engine file="Bristol-739">
    <location unit="IN">
      <x> -112.35748</x>
      <y> -165.24724 </y>
      <z> 38.772047 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
     <feed>1</feed>
    <thruster file="Rotol">
     <location unit="IN">
       <x> -112.35748 </x>
       <y> -165.24724 </y>
       <z> 38.772047 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
     <sense> -1 </sense>
    <p_factor> 60</p_factor>
    </thruster>
  </engine>

   <engine file="Bristol-739">
    <location unit="IN">
      <x> -112.35748 </x>
      <y> 165.24724 </y>
      <z> 38.772047 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
     <feed>0</feed>
    <feed>1</feed>
    <thruster file="Rotol">
     <location unit="IN">
       <x> -112.35748 </x>
       <y> 165.24724 </y>
       <z> 38.772047 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
     <sense> -1 </sense>
     <p_factor> 60</p_factor>
    </thruster>
  </engine>

   <engine file="MarboreII">
    <location unit="IN">
      <x> 75.944882 </x>
      <y> -642.63386</y>
      <z> 66.322835 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>2</feed>
     <feed>3</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 75.944882 </x>
       <y> -642.63386 </y>
       <z> 66.322835 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="MarboreII">
    <location unit="IN">
      <x> 75.944882 </x>
      <y> 642.63386 </y>
      <z> 66.322835 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
     <feed>2</feed>
    <feed>3</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 75.944882 </x>
       <y> 642.63386 </y>
       <z> 66.322835 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 0.0 </x>
       <y>   0.00 </y>
       <z> 60</z>
     </location>
     <capacity unit="LBS"> 6000 </capacity>
     <contents unit="LBS"> 3000 </contents>
  </tank>

  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 0.0 </x>
       <y>   0.00 </y>
       <z> 60 </z>
     </location>
     <capacity unit="LBS"> 6000 </capacity>
     <contents unit="LBS"> 3000 </contents>
  </tank>

  <tank type="FUEL" number="3">
     <location unit="IN">
       <x> 0.0 </x>
       <y>   0.00 </y>
       <z> -50 </z>
     </location>
     <capacity unit="LBS"> 1000 </capacity>
     <contents unit="LBS"> 500 </contents>
  </tank>

  <tank type="FUEL" number="4">
     <location unit="IN">
       <x> 0.0 </x>
       <y>   0.00 </y>
       <z> -21.63 </z>
     </location>
     <capacity unit="LBS"> 1000</capacity>
     <contents unit="LBS"> 500 </contents>
  </tank>

 </propulsion>
 
        <system file="pitch"/>
        <system file="roll"/>
        <system file="yaw"/>
        <system file="flaps"/>
        <system file="landing-gear"/>
        <system file="speedbrake"/>
        <system file="throttle2"/>
        <system file="propeller"/>
        <system file="turbine"/>
        <system file="fuel"/>
        <system file="external"/>
        <system file="electric-master"/>
        <system file="outdoor-lighting"/>
        <system file="mixture-control"/>

 <flight_control name="FCS: Nord 2502">
 </flight_control>

 <aerodynamics>

     <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	1.2000
                          0.1000	1.1500
                          0.1500	1.0900
                          0.2000	1.0200
                          1.1000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>

        <function name="aero/function/kCLpw">
        <description>Change_in_lift_due_to_propeller_wash</description>
        <product>
                <table>
                    <independentVar lookup="row" >aero/qbar-psf</independentVar>
                    <independentVar lookup="column">propulsion/engine/thrust-coefficient</independentVar>
                    <tableData>
                                    0.000   0.040
                        00.0000	    1.000   1.410
                        50.0000	    1.000   1.000
                    </tableData>
                </table>
            </product>
        </function>
<documentation>
    must be improved
    this is a try : the propellerwash effect on the wing, at low speed
    that lift effect is maximum when the qbar-psf is close to zero and propeller thrust to maximum (here 0.04)
    that effect is null when qbar-psf is 50 (100 kts) or propeller thrust close to zero
    we suppose that both engines are running
</documentation>




  <axis name="LIFT">
    <function name="aero/coefficient/CLalpha">
      <description>Lift_due_to_alpha</description>
      <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
           <property>aero/function/kCLpw</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
                -0.2000	-0.6800
                -0.0900	-0.2200
                0.0000	0.2700
                0.0900	0.9300
                 0.1000	1.1300
                 0.1200	1.2500
                 0.2400	1.5500
                 0.2600	1.6400
                 0.2800	1.6700
                 0.3000	1.6300
                 0.3600	1.3500
            </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-norm</property>
            <property>aero/function/kCLpw</property>
           <value> 0.6</value>
       </product>
    </function>

    <!--<function name="aero/coefficient/dCLsb">
       <description>Delta_Lift_due_to_speedbrake</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>-0.08</value>
       </product>
    </function>-->

    <function name="aero/coefficient/CLde">
       <description>Lift_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-rad</property>
           <value>0.2</value>
       </product>
    </function>




  </axis>

  <axis name="DRAG">

    <function name="aero/coefficient/CD0">
       <description>Drag_at_zero_lift</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
                -1.57       1.500
                -0.26    0.022
                0.00    0.017
                0.26    0.022
                1.57       1.500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDi">
       <description>Induced_drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.034</value>
         </product>
    </function>

    <function name="aero/coefficient/CDmach">
       <description>Drag_due_to_mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.79      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/coefficient/CDflap">
       <description>Drag_due_to_flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-norm</property>
           <value>0.0500</value>
         </product>
    </function>

    <function name="aero/coefficient/CDgear">
       <description>Drag_due_to_gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.011</value>
         </product>
    </function>

    <!--<function name="aero/coefficient/CDsb">
       <description>Drag_due_to_speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0.017</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>

  <axis name="SIDE">

    <function name="aero/coefficient/CYb">
       <description>Side_force_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/beta-rad</property>
           <value>-1</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/coefficient/Clb">
       <description>Roll_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>-0.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Clp">
       <description>Roll_moment_due_to_roll_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/p-aero-rad_sec</property>
           <value>-0.4</value>
       </product>
    </function>

    <function name="aero/coefficient/Clr">
       <description>Roll_moment_due_to_yaw_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>0.15</value>
       </product>
    </function>

    <function name="aero/coefficient/Clda">
       <description>Roll_moment_due_to_aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.100
              2.0    0.033
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cldr">
       <description>Roll_moment_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>0.01</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/coefficient/Cmalpha">
       <description>Pitch_moment_due_to_alpha</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/alpha-rad</property>
           <value>-0.7</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmde">
       <description>Pitch_moment_due_to_elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.300
              2.0     -0.325
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cmdf">
       <description>Pitch_moment_due_to_flap</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/flap-pos-deg</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     0
              2.0     0.001
            </tableData>
          </table>
       </product>
    </function>


    <function name="aero/coefficient/Cmq">
       <description>Pitch_moment_due_to_pitch_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/ci2vel</property>
           <property>velocities/q-aero-rad_sec</property>
           <value>-21</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmadot">
       <description>Pitch_moment_due_to_alpha_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/ci2vel</property>
           <property>aero/alphadot-rad_sec</property>
           <value>-4</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <function name="aero/coefficient/Cnb">
       <description>Yaw_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>0.12</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnr">
       <description>Yaw_moment_due_to_yaw_rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>-0.15</value>
       </product>
    </function>

    <function name="aero/coefficient/Cndr">
       <description>Yaw_moment_due_to_rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnda">
       <description>Adverse_yaw</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/left-aileron-pos-rad</property>
           <value>0</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>
