<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>

<fdm_config name="Ercoupe" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Ron Jensen, Erik Hofman,  DATCOM+ and Aeromatic v 3.3.10 </author>
  <filecreationdate> 27 May 2008 </filecreationdate>
  <version>$Revision: 1.26 $</version>
  <description> Models a Ercoupe. </description>
 </fileheader>

<!--
  File:     Ercoupe.xml
  Inputs:
    name:          Ercoupe
    type:          Single engine Glider, Small Commuter
    stall speed:   30.10kts
    max weight:    1260.00 lb
    length:        20.75 ft
    wing: 
     span:         30.00 ft
     area:         142.60 sq-ft
     mean chord:   5.11 ft
     aspect ratio: 6.31:1
     taper ratio:  1.00:1
     incidence:    2.50 degrees
     dihedral:     7.00 degrees
     sweep:        0.00 degrees

    no. engines:   1
    engine type:   Piston Engine
    engine layout: forward fuselage

    gear type:     tricycle
    steering type: steering
    retractable?:  no

  Outputs:
    wing loading:       8.84 lb/sq-ft
     - thickness ratio: 11.02%
    payload:            235.52 lbs
    CL-alpha:           4.83 per radian
    CL-0:               0.36
    CL-max:             1.71
    CD-0:               0.02
    K:                  0.04
    Mcrit:              0.70
-->


<!--
    References:

    NACA Technical Note No. 1801,
    Walter J. Klinar and Lawrence J. Gale
    "Wind-tunnel investigation of the spinning characteristics of a model of a
     twin-tail low-wing personal-owner-type airplane with linked and unlinked
     rudder and aileron controls"

    NACA Technical Note No. 3671
    Horace F. Emerson
    "Wind-tunnel investigation of the effect of clipping the tips of
     triangular wings of different thickness, camber, and aspect ratio -
     transonic bump method"

    NACA Technical Note No. 3676
    Fred. E. Weick and Norman Abramson
    "Investigation of lateral control near the stall - Flight tests with
     high-wing and low-wing monoplanes of various configurations"

    Airplane Stability and Control, Second Edition
    Malcolm J. Abzug and E. Eugene Larrabee
    Chapter 15: "Safe Personal Airplanes"
-->

 <metrics>
   <wingarea  unit="FT2">   142.60 </wingarea>
   <wingspan  unit="FT" >    30.00 </wingspan>
   <wing_incidence unit="DEG"> 2.50 </wing_incidence>
   <chord     unit="FT" >     5.11 </chord>
   <htailarea unit="FT2">    19.60 </htailarea>
   <htailarm  unit="FT" >    13.25 </htailarm>
   <vtailarea  unit="FT2">    9.30 </vtailarea>
   <vtailarm  unit="FT" >    13.25 </vtailarm>
   <location name="AERORP" unit="IN">
     <x>    93.36 </x>
     <y>     0.00 </y>
     <z>     0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>   100.73 </x>
     <y>   -18.00 </y>
     <z>    20.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>  100.7 </x>
     <y>    0.0 </y>
     <z>   23.6 </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    426.87 </ixx>
   <iyy unit="SLUG*FT2">    363.05 </iyy>
   <izz unit="SLUG*FT2">    738.99 </izz>
   <emptywt unit="LBS" >    838.00 </emptywt>
   <location name="CG" unit="IN">
     <x>    93.36 </x>
     <y>     0.00 </y>
     <z>    -6.23 </z>
   </location>

   <pointmass name="Pilot">
        <weight unit="LBS"> 170 </weight>
        <location unit="IN">
            <x>100.73 </x>
            <y>-18.00 </y>
            <z> -7.05 </z>
        </location>
    </pointmass>
    <pointmass name="Co-Pilot">
        <weight unit="LBS"> 0 </weight>
        <location unit="IN">
            <x>100.73 </x>
            <y> 18.00 </y>
            <z> -7.05 </z>
        </location>
    </pointmass>
    <pointmass name="Luggage">
        <!-- Max Luggage = 65 LBS -->
        <weight unit="LBS"> 25 </weight>
        <location unit="IN">
            <x>135 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
   </pointmass>
 </mass_balance>

 <propulsion>

   <engine file="c-75-12">
    <location unit="IN">
      <x>    43.26 </x>
      <y>     0.00 </y>
      <z>     0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch>     0.00 </pitch>
       <roll>     0.00 </roll>
        <yaw>     0.00 </yaw>
    </orient>
    <feed> 0 </feed>

    <thruster file="prop_mccauley_7557">
     <sense> 1 </sense>
     <location unit="IN">
       <x>    43.26 </x>
       <y>     0.00 </y>
       <z>     0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch>     0.00 </pitch>
        <roll>     0.00 </roll>
         <yaw>     0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- fuselage fuel -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x>  71.26</x>
       <y>   0.00 </y>
       <z>   0.00 </z>
     </location>
     <capacity unit="LBS"> 30.00 </capacity>
     <contents unit="LBS">  30.00 </contents>
  </tank>
<!-- left wing fuel -->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x>  93.36</x>
       <y> -32.00 </y>
       <z>  -6.23</z>
     </location>
     <capacity unit="LBS"> 54.00 </capacity>
     <contents unit="LBS">  54.00 </contents>
  </tank>
<!-- right wing fuel -->
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x>  93.36</x>
       <y>  32.00 </y>
       <z>  -6.23</z>
     </location>
     <capacity unit="LBS"> 54.00 </capacity>
     <contents unit="LBS">  54.00 </contents>
  </tank>

 </propulsion>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
    <location unit="IN">
      <x>    43.26 </x>
      <y>     0.00 </y>
      <z>   -26.00 </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">     678.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 589.00 </damping_coeff>
    <max_steer unit="DEG"> 45.00 </max_steer>
    <brake_group> NONE </brake_group>
    <retractable> 0 </retractable>
  </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
    <location unit="IN">
      <x>   100.73 </x>
      <y>   -32.60 </y>
      <z>   -25.55 </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">     1260.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 630.00 </damping_coeff>
    <max_steer unit="DEG">0</max_steer>
    <brake_group> LEFT </brake_group>
    <retractable> 0 </retractable>
  </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
    <location unit="IN">
      <x>   100.73 </x>
      <y>    32.60 </y>
      <z>   -25.55 </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">     1260.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 630.00 </damping_coeff>
    <max_steer unit="DEG">0</max_steer>
    <brake_group> RIGHT </brake_group>
    <retractable> 0 </retractable>
  </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x>    93.36 </x>
     <y>  -180.00 </y>
     <z>    -6.23 </z>
    </location>
   <static_friction>  1 </static_friction>
   <dynamic_friction> 1 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      1260.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 1260.00 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x>    93.36 </x>
     <y>   180.00 </y>
     <z>    -6.23 </z>
    </location>
   <static_friction>  1 </static_friction>
   <dynamic_friction> 1 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      1260.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 1260.00 </damping_coeff>
  </contact>

 </ground_reactions>

 <system file="Controls.xml"/>
 <system file="Landing Gear.xml"/>
 <system file="speedbrakes.xml"/>

 <flight_control name="FCS: Ercoupe">

 </flight_control>

 <aerodynamics>

  <alphalimits unit="DEG">
   <min>-5.0</min>
   <max>14.0</max>
  </alphalimits>

  <hysteresis_limits unit="DEG">
   <min> 5.0</min>
   <max>20.0</max>
  </hysteresis_limits>

  <function name="aero/function/ground-effect-factor-lift">
   <description>Change in lift due to ground effect factor</description>
    <table>
     <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
     <tableData>
        0.0  1.203
        0.1  1.127
        0.15 1.090
        0.2  1.073
        0.3  1.046
        0.4  1.055
        0.5  1.019
        0.6  1.013
        0.7  1.008
        0.8  1.006
        0.9  1.003
        1.0  1.002
        1.1  1.0
     </tableData>
    </table>
  </function>

  <function name="aero/function/ground-effect-factor-drag">
   <description>Change in drag due to ground effect</description>
    <table>
     <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
     <tableData>
        0.0  0.480
        0.1  0.515
        0.15 0.629
        0.2  0.709
        0.3  0.815
        0.4  0.882
        0.5  0.928
        0.6  0.962
        0.7  0.988
        0.8  1.0
        0.9  1.0
        1.0  1.0
        1.1  1.0
     </tableData>
    </table>
  </function>

  <axis name="LIFT">

    <function name="aero/force/Lift_propwash">
      <description>Delta lift due to propeller induced velocity</description>
      <product>
          <property>aero/function/ground-effect-factor-lift</property>
          <property>propulsion/engine[0]/thrust-coefficient</property>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
                     0.0     60.0
              -0.24  0.000   0.000
               0.00  0.072   0.192
               0.30  0.341   0.911
               0.59  0.000   0.000
            </tableData>
          </table>
      </product>
    </function>

    <!-- Lift above 0.85 and below -0.85 is generalised -->
    <function name="aero/force/Lift_alpha">
      <description>Lift due to alpha</description>
      <product>
          <property>aero/function/ground-effect-factor-lift</property>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -1.57  0.0000
              -1.22 -0.5764
              -1.05 -0.7765
              -0.88 -0.8967
              -0.67 -0.4735
              -0.31 -1.1838
              -0.200 -0.750
              -0.001 -0.013
               0.112  0.722
               0.125  0.766
               0.142  0.842
               0.159  0.931
               0.185  1.121
               0.219  1.279
               0.260  1.438
               0.307  1.514
               0.324  1.483
               0.334  1.407
               0.350  1.193
               0.420  0.398
               0.60  0.7899
               0.88  1.1033
               1.05  0.9555
               1.22  0.7092
               1.57  0.0000
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/force/Lift_pitch_rate">
        <description>Lift due to pitch rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>velocities/q-aero-rad_sec</property>
          <property>aero/ci2vel</property>
          <value> 2.8516 </value>
        </product>
      </function>

      <function name="aero/force/Lift_alpha_rate">
        <description>Lift due to alpha rate</description>
        <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/alphadot-rad_sec</property>
           <property>aero/ci2vel</property>
           <table>
             <independentVar lookup="row">aero/alpha-deg</independentVar>
             <tableData>
               -16.00   .5344E-02
               -8.000   .5773E-02
               -6.000   .5917E-02
               -4.000   .5970E-02
               -2.000   .5994E-02
                 .000   .6122E-02
                2.000   .6405E-02
                4.000   .6727E-02
                8.000   .7359E-02
                9.000   .7476E-02
                10.00   .7514E-02
                12.00   .7000E-02
                14.00   .5970E-02
                16.00   .4805E-02
                18.00   .3796E-02
                19.00   .3333E-02
                20.00   .2706E-02
                21.00   .1945E-02
                22.00   .3998E-04
                30.00  -.1241E-01
             </tableData>
           </table>
        </product>
      </function>

    <function name="aero/force/Lift_elevator">
       <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> 0.3686 </value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/force/Drag_alpha">
       <description>Drag due to alpha</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
            <tableData>
             -1.570  1.5000
             -0.140  0.0456
             -0.105  0.0320
             -0.070  0.0231
             -0.035  0.0185
              0.000  0.0177
              0.035  0.0206
              0.070  0.0278
              0.140  0.0563
              0.157  0.0666
              0.175  0.0784
              0.209  0.1063
              0.244  0.1389
              0.279  0.1695
              0.314  0.1993
              0.332  0.2132
              0.349  0.2264
              0.367  0.2381
              0.384  0.2477
              1.570  1.5000
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_induced">
       <description>Induced drag</description>
         <product>
           <property>aero/function/ground-effect-factor-drag</property>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value> 0.0531 </value>
         </product>
    </function>

    <function name="aero/force/Drag_mach">
       <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    0.0000
                0.70    0.0000
                1.10    0.0230
                1.80    0.0150
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/force/Drag_beta">
       <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    1.2300
              -0.26    0.0500
               0.00    0.0000
               0.26    0.0500
               1.57    1.2300
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_elevator">
       <description>Drag due to Elevator Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-rad</property></abs>
           <value> 0.0400 </value>
       </product>
    </function>

    <function name="aero/force/Drag_speedbrake">
       <description>Drag_due_to_speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>/surface-positions/speedbrake-pos-norm</property>
           <value>0.007</value>
         </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/force/Side_beta">
       <description>Side force due to beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/beta-rad</property>
           <value> -0.2978 </value>
       </product>
    </function>
    <function name="aero/force/Side_roll_rate">
       <description>Side force due to roll rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/bi2vel</property>
           <property>velocities/p-aero-rad_sec</property>
           <table>
             <independentVar lookup="row">aero/Re</independentVar>
             <tableData>
                 2148934   0.3097
                 2363827   0.0264
                 3223401   0.0117
                 4319461   0.0065
             </tableData>
           </table>
       </product>
    </function>

    <function name="aero/force/Side_yaw_rate">
       <description>Side force due to yaw rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value> 0.2630 </value>
       </product>
    </function>

    <function name="aero/force/Side_rudder">
       <description>Side force due to rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/rudder-pos-rad</property>
           <value> 0.0917 </value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/moment/Pitch_propwash">
      <description>Pitch moment due to propeller induced velocity</description>
      <product>
          <property>propulsion/engine[0]/thrust-coefficient</property>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
                     0.0     60.0
              -0.01  0.000   0.000
               0.00  0.026   0.068
               0.30  0.122   0.325
               0.39  0.000   0.000
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/moment/Pitch_alpha">
       <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>
           <table>
            <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
            <tableData>
             -0.279   0.1663
             -0.140   0.0767
             -0.105   0.0561
             -0.070   0.0369
             -0.035   0.0176
              0.000  -0.0023
              0.035  -0.0247
              0.070  -0.0505
              0.140  -0.1081
              0.157  -0.1221
              0.175  -0.1372
              0.209  -0.1722
              0.244  -0.2076
              0.279  -0.2220
              0.314  -0.2252
              0.332  -0.2260
              0.349  -0.2284
              0.367  -0.2292
              0.384  -0.2292
              0.524  -0.1279
          </tableData>
        </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_elevator">
       <description>Pitch moment due to elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
           <table>
             <independentVar lookup="row">fcs/elevator-pos-deg</independentVar>
             <tableData>
               -20.00   .6657E-01
               -15.00   .6280E-01
               -10.00   .4478E-01
               -5.000   .2239E-01
                 .000  -.4478E-04
                5.000  -.2239E-01
                10.00  -.4478E-01
                13.00  -.5667E-01
                16.00  -.6524E-01
             </tableData>
           </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_damp">
       <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> -7.3941 </value>
       </product>
    </function>

    <function name="aero/moment/Pitch_alphadot">
       <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>
         <table>
           <independentVar lookup="row">aero/alpha-wing-rad</independentVar>
           <tableData>
             -0.2793  -0.5461
             -0.1396  -0.5901
             -0.1047  -0.6045
             -0.0698  -0.6102
             -0.0349  -0.6125
              0.0000  -0.6257
              0.0349  -0.6543
              0.0698  -0.6875
              0.1396  -0.7523
              0.1571  -0.7638
              0.1745  -0.7678
              0.2094  -0.7156
              0.2443  -0.6102
              0.2793  -0.4910
              0.3142  -0.3879
              0.3316  -0.3406
              0.3491  -0.2765
              0.3665  -0.1988
              0.3840  -0.0041
              0.5236  -1.2685
           </tableData>
        </table>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

   <function name="aero/moment/Roll_differential_propwash">
       <description>Roll moment due to differential propwash</description>
       <product>
           <property>propulsion/engine[0]/thrust-coefficient</property>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <table>
             <independentVar lookup="row">aero/alpha-rad</independentVar>
             <tableData>
             -1.0 -0.1445
              0.0  0.0325
              1.0  0.1445
             </tableData>
        </table>
       </product>
    </function>

    <function name="aero/moment/Roll_beta">
       <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>
           <table>
             <independentVar lookup="row">aero/alpha-rad</independentVar>
             <tableData>
               -0.2793  0.1110
               -0.1396  0.0472
               -0.1047  0.0316
               -0.0698  0.0166
               -0.0349  0.0024
                0.0000 -0.0110
                0.0349 -0.0250
                0.0698 -0.0400
                0.1396 -0.0717
                0.1571 -0.0800
                0.1745 -0.0885
                0.2094 -0.1056
                0.2443 -0.1219
                0.2793 -0.1338
                0.3142 -0.1432
                0.3316 -0.1467
                0.3491 -0.1495
                0.3665 -0.1514
                0.3840 -0.1522
                0.5236  0.0729
             </tableData>
           </table>
       </product>
    </function>

    <function name="aero/moment/Roll_damp">
       <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> -0.6327 </value>
       </product>
    </function>

    <function name="aero/moment/Roll_yaw">
       <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>
           <property>fcs/gear-no-wow</property>
           <table>
             <independentVar lookup="row">aero/alpha-rad</independentVar>
             <independentVar lookup="column">aero/Re</independentVar>
             <tableData>
                          2148934  2363827  3223401  4319461
                 -0.0349   0.0390   0.0390   0.0390   0.0390
                  0.3491   4.2591   0.5031   0.5031   0.5031
             </tableData>
           </table>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron">
       <description>Roll moment due to aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <table>
            <independentVar lookup="row">fcs/left-aileron-pos-deg</independentVar>
            <tableData>
             -64.00  -0.09735
             -40.00  -0.08178
             -20.00  -0.04764
             -10.00  -0.02382
               .000   0.000
              10.00   0.02382
              20.00   0.04764
              40.00   0.08178
              64.00   0.09735
           </tableData>
         </table>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder">
       <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="YAW">

    <function name="aero/moment/Yaw_beta">
       <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> 0.0632 </value>
       </product>
    </function>

    <function name="aero/moment/Yaw_roll_rate">
       <description>Yaw 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-rad_sec</property>
           <table>
             <independentVar lookup="row">aero/Re</independentVar>
             <tableData>
                 2148934  -0.1368
                 2363827  -0.0117
                 3223401  -0.0052
                 4319461  -0.0029
             </tableData>
           </table>
       </product>
    </function>

    <function name="aero/moment/Yaw_damp">
       <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> -0.0698 </value>
       </product>
    </function>

    <function name="aero/moment/Yaw_rudder">
       <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>-0.0405</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_aileron">
       <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> -0.0100 </value>
       </product>
    </function>

  </axis>

 </aerodynamics>

 <external_reactions>
 </external_reactions>

</fdm_config>
