aircraft/dr1/dr1.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Fokker Dr.1" 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, Aeromatic v 0.9 </author>
  <filecreationdate> 2008-07-26 </filecreationdate>
  <version>$Revison: $</version>
  <description> Models a Fokker Dr.1. </description>
 </fileheader>

<!--
  File:     Fokker Dr.1.xml
  Inputs:
    name:          Fokker Dr.1
    type:          WW1 type
    max weight:    1292.13 lb
    wing span:     23.6232 ft
    length:        18.93137 ft
    wing area:     201.3055 sq-ft
    gear type:     taildragger
    retractable?:  no
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  6.42 lb/sq-ft
    CL-alpha:      5 per radian
    CL-0:          0.25
    CL-max:        1.4
    CD-0:          0.0323
    K:             0.04

-->

 <metrics>
   <wingarea  unit="FT2">  201.31 </wingarea>
   <wingspan  unit="FT" >   23.62 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >    8.52 </chord>
   <htailarea unit="FT2">   32.21 </htailarea>
   <htailarm  unit="FT" >    9.84 </htailarm>
   <vtailarea unit="FT2">   20.13 </vtailarea>
   <vtailarm  unit="FT" >    9.47 </vtailarm>
   <location name="AERORP" unit="IN">
     <x>   0.00</x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  29.53 </x>
     <y> -18.00 </y>
     <z>  45.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    368.55 </ixx>
   <iyy unit="SLUG*FT2">    522.24 </iyy>
   <izz unit="SLUG*FT2">    731.37 </izz>
   <emptywt unit="LBS" >       895 </emptywt>
   <location name="CG" unit="IN">
     <x>   0.00 </x>
     <y>   0.00 </y>
     <z>  -5.68 </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>  -8.66 </x>
     <y> -30.32 </y>
     <z> -76.77 </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">      1000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  500 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x>  -8.66 </x>
     <y>  30.32 </y>
     <z> -76.77 </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">       1000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   500 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>

  <contact type="BOGEY" name="TAIL_SKID">
   <location unit="IN">
     <x> 162.20 </x>
     <y>   0.00 </y>
     <z> -26.77 </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">       200 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  100 </damping_coeff>
   <max_steer unit="DEG"> 0.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>

  <contact type="STRUCTURE" name="TAIL">
   <location unit="IN">
     <x> 173.23 </x>
     <y>   0.00 </y>
     <z>  -9.45 </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">       200 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  100 </damping_coeff>
   <max_steer unit="DEG"> 0.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>

  <contact type="STRUCTURE" name="RUDDER_TOP">
   <location unit="IN">
     <x> 173.23 </x>
     <y>   0.00 </y>
     <z>  16.93 </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">       200 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  100 </damping_coeff>
   <max_steer unit="DEG"> 0.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
  </contact>

  <contact type="STRUCTURE" name="LEFT_UPPER_WING">
    <location unit="IN">
     <x>    0.0 </x>
     <y> -133.9 </y>
     <z>   35.8 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">        300 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   150 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_UPPER_WING">
    <location unit="IN">
     <x>    0.0 </x>
     <y>  133.9 </y>
     <z>   35.8 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">        300 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   150 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="LEFT_LOWER_WING">
    <location unit="IN">
     <x>   -8.7 </x>
     <y> -112.2 </y>
     <z>  -33.5 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">        300 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   150 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_LOWER_WING">
    <location unit="IN">
     <x>   -8.7 </x>
     <y>  112.2 </y>
     <z>  -33.5 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">        300 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   150 </damping_coeff>
  </contact>

 </ground_reactions>

 <external_reactions>
  <force name="pushback" frame="BODY">
   <location unit="IN">
     <x> 173.23 </x>
     <y>   0.00 </y>
     <z>  -9.45 </z>
   </location>
   <direction>
    <x>1</x>
    <y>0</y>
    <z>0</z>
   </direction>
  </force>
 </external_reactions>

 <propulsion>

   <engine file="Oberursel-UrII">
    <location unit="IN">
      <x> -18.90 </x>
      <y>   0.00 </y>
      <z> -16.14 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="Dr1_propeller">
     <location unit="IN">
       <x> -36.36 </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>
     <sense> -1 </sense>
     <p_factor> 60 </p_factor>
    </thruster>
  </engine>

  <tank type="FUEL" number="0">
     <location unit="IN">
       <x>  -5.91 </x>
       <y>   0.00 </y>
       <z>  -7.09 </z>
     </location>
     <capacity unit="LBS"> 125.00 </capacity>
     <contents unit="LBS">  50.00 </contents>
  </tank>

 </propulsion>

 <system file="pushback"/>
 <!-- <system file="chocks"/> -->

 <flight_control name="FCS: Fokker Dr.1">

  <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> -0.31 </min>
        <max>  0.26 </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> -0.30 </min>
        <max>  0.30 </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> -0.30 </min>
        <max>  0.30 </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> -0.30 </min>
        <max>  0.30 </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> -0.30 </min>
        <max>  0.30 </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> -0.44 </min>
        <max>  0.44 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.44 </min>
        <max>  0.44 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

  </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-deg</independentVar>
            <tableData>
		-180.000000    0
		-167.283800    0.507559
		-165.091352    0.503240
		-160.267966    0.460043
		-158.075518    0.451404
		-155.883069    0.460043
		-150.182704    0.498920
		-140.535932    0.498920
		-124.311815    0.451404
		-113.349574    0.356371
		-103.702801    0.239741
		-94.056029     0.084233
		-85.000000     -0.053212
		-83.000000     -0.075185
		-79.000000     -0.119132
		-75.000000     -0.163079
		-71.000000     -0.207027
		-67.000000     -0.250974
		-63.000000     -0.294921
		-59.000000     -0.330791
		-55.000000     -0.362833
		-51.000000     -0.394875
		-49.000000     -0.410896
		-45.000000     -0.442939
		-43.000000     -0.458960
		-41.000000     -0.474981
		-39.000000     -0.492972
		-35.000000     -0.530579
		-31.000000     -0.568186
		-29.000000     -0.586989
		-27.000000     -0.605792
		-25.000000     -0.620705
		-23.000000     -0.633666
		-21.000000     -0.619398
		-19.000000     -0.593683
		-17.000000     -0.562693
		-15.000000     -0.531727
		-13.000000     -0.506665
		-11.000000     -0.430152
		-9.000000      -0.305751
		-7.000000      -0.181350
		-5.000000      -0.056949
		-3.000000       0.067354
		-1.000000       0.191575
		1.000000        0.315796
		3.000000        0.440017
		5.000000        0.564237
		7.000000        0.689083
		9.000000        0.814508
		11.000000       0.927432
		13.000000       1.016563
		15.000000       1.074647
		17.000000       1.044252
		19.000000       0.916713
		21.000000       0.742705
		23.000000       0.655686
		25.000000       0.615506
		27.000000       0.592442
		29.000000       0.569378
		31.000000       0.552969
		33.000000       0.542580
		35.000000       0.532191
		37.000000       0.521802
		39.000000       0.511413
		41.000000       0.499081
		43.000000       0.486002
		45.000000       0.472923
		47.000000       0.459843
		49.000000       0.446764
		51.000000       0.433685
		53.000000       0.420605
		55.000000       0.406311
		57.000000       0.388495
		59.000000       0.370678
		61.000000       0.352862
		63.000000       0.335045
		65.000000       0.317229
		67.000000       0.299343
		69.000000       0.276179
		71.000000       0.253014
		73.000000       0.229849
		75.000000       0.206684
		77.000000       0.183520
		79.000000       0.160355
		81.000000       0.135592
		83.000000       0.105045
		85.000000       0.074498
		90.548112       0.002160
		104.141291      -0.218143
		122.119367      -0.399568
		136.589525      -0.455724
		150.621194      -0.451404
		155.883069      -0.416847
		157.637028      -0.412527
		159.390987      -0.425486
		163.775883      -0.455724
		165.968331      -0.468683
		167.722290      -0.447084
		180.000000      0
            </tableData>
          </table>
      </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>

    <function name="aero/coefficient/CLadot">
       <description>Delta_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>
           <value>0.759</value>
       </product>
    </function>

    <function name="aero/coefficient/CLq">
       <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>1.245</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">
    <!--
       CDK:	0.0922
     -->
    <function name="aero/coefficient/CDo">
       <description>Drag_at_zero_lift</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <value>0.0323</value>
       </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>
           <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
		-180.000000     0.036717
		-169.914738     0.062635
		-150.182704     0.153348
		-122.119367     0.265659
		-84.847747      0.408207
		-45.383678      0.533477
		-43.000000      0.527482
		-41.000000      0.530885
		-39.000000      0.534288
		-37.000000      0.528571
		-35.000000      0.513248
		-33.000000      0.497924
		-31.000000      0.482600
		-29.000000      0.467276
		-27.000000      0.451953
		-25.000000      0.416920
		-23.000000      0.374764
		-21.000000      0.332608
		-19.000000      0.290452
		-17.000000      0.238177
		-15.000000      0.175336
		-13.000000      0.085176
		-11.000000      0.029907
		-9.000000       0.002152
		-7.000000       0.001623
		-5.000000       0.001818
		-3.000000       0.002013
		-1.000000       0.002207
		1.000000        0.002402
		3.000000        0.002597
		5.000000        0.002792
		7.000000        0.002986
		9.000000        0.003181
		11.000000       0.003376
		13.000000       0.013600
		15.000000       0.032951
		17.000000       0.060633
		19.000000       0.092297
		21.000000       0.123961
		23.000000       0.157220
		25.000000       0.200529
		27.000000       0.243839
		29.000000       0.287148
		31.000000       0.330457
		33.000000       0.364475
		35.000000       0.398403
		37.000000       0.432331
		39.000000       0.466259
		41.000000       0.500187
		43.000000       0.533927
		45.000000       0.551580
		47.000000       0.569232
		49.000000       0.586885
		51.000000       0.604537
		53.000000       0.622189
		55.000000       0.638904
		57.000000       0.645843
		59.000000       0.652782
		61.000000       0.655156
		63.000000       0.645551
		65.000000       0.635947
		67.000000       0.625216
		69.000000       0.603688
		71.000000       0.582160
		73.000000       0.560632
		75.000000       0.539104
		77.000000       0.508452
		79.147381       0.481641
		100.633374      0.334773
		132.643118      0.192225
		160.706456      0.079914
		180.000000      0.036717
            </tableData>
          </table>
         </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/mag-elevator-pos-rad</property>
           <value>0.0136</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/coefficient/CYbeta">
       <description>Side_force_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/beta-rad</property>
           <value>-0.3855</value>
       </product>
    </function>

    <function name="aero/coefficient/CYda">
       <description>Side_force_due_to_aileron</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/left-aileron-pos-rad</property>
           <value>0.0000</value>
       </product>
    </function>

    <function name="aero/coefficient/CYdr">
       <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>0.094</value>
       </product>
    </function>

    <function name="aero/coefficient/CYp">
       <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>
           <value>-0.01</value>
       </product>
    </function>

    <function name="aero/coefficient/CYr">
        <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>0.1047</value>
        </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/coefficient/Clbeta">
       <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>-0.02</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>-0.193</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>-0.0458</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>
          <value>0.087</value>
       </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>-0.005</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>
           <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
		-180.000000    0.002160
		-155.444580    0.049676
		-127.381242    0.088553
		-84.847747     0.118790
		-83.000000     0.111578
		-81.000000     0.109529
		-79.000000     0.107307
		-77.000000     0.104574
		-75.000000     0.101924
		-73.000000     0.099422
		-71.000000     0.097083
		-69.000000     0.094282
		-67.000000     0.091509
		-65.000000     0.088937
		-63.000000     0.086618
		-61.000000     0.084993
		-59.000000     0.084405
		-57.000000     0.084065
		-55.000000     0.083979
		-53.000000     0.084150
		-51.000000     0.084585
		-49.000000     0.085133
		-47.000000     0.084831
		-45.000000     0.084135
		-43.000000     0.083629
		-41.000000     0.083319
		-39.000000     0.082857
		-37.000000     0.081386
		-35.000000     0.078832
		-33.000000     0.076293
		-31.000000     0.073780
		-29.000000     0.070542
		-27.000000     0.066352
		-25.000000     0.059782
		-23.000000     0.052199
		-21.000000     0.048019
		-19.000000     0.036628
		-17.000000     0.008613
		-15.000000     -0.021966
		-13.000000     -0.051723
		-11.000000     -0.061373
		-9.000000      -0.055043
		-7.000000      -0.042039
		-5.000000      -0.030525
		-3.000000      -0.020684
		-1.000000      -0.012551
		1.000000       -0.006150
		3.000000       -0.001511
		5.000000       0.001345
		7.000000       0.002421
		9.000000       0.001690
		11.000000      -0.001231
		13.000000      -0.004202
		15.000000      -0.006967
		17.000000      -0.015326
		19.000000      -0.039137
		21.000000      -0.053761
		23.000000      -0.057517
		25.000000      -0.059092
		27.000000      -0.059484
		29.000000      -0.057321
		31.000000      -0.055292
		33.000000      -0.055424
		35.000000      -0.055607
		37.000000      -0.055193
		39.000000      -0.054363
		41.000000      -0.053475
		43.000000      -0.052650
		45.000000      -0.054951
		47.000000      -0.057268
		49.000000      -0.059612
		51.000000      -0.061994
		53.000000      -0.063932
		55.000000      -0.065632
		57.000000      -0.068524
		59.000000      -0.071343
		61.000000      -0.074801
		63.000000      -0.079945
		65.000000      -0.084862
		67.000000      -0.089696
		69.000000      -0.094872
		71.000000      -0.099632
		73.000000      -0.103974
		75.000000      -0.107735
		77.000000      -0.111800
		79.000000      -0.115339
		81.000000      -0.117895
		83.000000      -0.116303
		85.724726      -0.110151
		121.680877     -0.079914
		154.567600     -0.041037
		180.000000     0.002160
            </tableData>
           </table>
       </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>
          <table>
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
            <tableData>
                       -0.35        0		0.35
              -180.000	0.015374    0.000000	-0.015374
              -163.145	0.100936    0.081551	0.065508
              -161.555	0.105615    0.084893	0.063503
              -159.965	0.103610    0.082219	0.057487
              -157.420	0.096257    0.076203	0.052807
              -155.512	0.092914    0.072193	0.056150
              -153.604	0.100267    0.075535	0.080214
              -146.608	0.129011    0.106283	0.121658
              -137.703	0.162433    0.139706	0.145053
              -124.028	0.187834    0.162433	0.154412
              -104.947	0.194519    0.172460	0.155080
              -91.227	0.195800    0.173500	0.153400
              -71.329	0.193000    0.165200	0.130500
              -53.688	0.186900    0.150800	0.105100
              -41.556	0.180900    0.135600	0.071000
              -34.678	0.176100    0.120200	0.076400
              -30.176	0.173500    0.113200	0.088700
              -25.540	0.176700    0.130300	0.084000
              -22.669	0.171600    0.132500	0.064600
              -16.566	0.151400    0.117400	0.015500
              -1.000	0.098300    0.000400	-0.099000
              6.800	0.042300   -0.040000	-0.136000
              14.848	-0.015500  -0.117400	-0.151400
              21.533	-0.064600  -0.132500	-0.171600
              24.758	-0.084000  -0.130300	-0.176700
              28.255	-0.088700  -0.113200	-0.173500
              30.402	-0.076400  -0.120200	-0.176100
              38.547	-0.071000  -0.135600	-0.180900
              54.266	-0.105100  -0.150800	-0.186900
              69.499	-0.130500  -0.165200	-0.193000
              89.241	-0.153400  -0.173500	-0.195800
              113.534	-0.154412  -0.172460	-0.194519
              128.481	-0.145053  -0.162433	-0.187834
              139.611	-0.121658  -0.139706	-0.162433
              150.424	-0.080214  -0.106283	-0.129011
              155.830	-0.056150  -0.075535	-0.100267
              157.739	-0.052807  -0.072193	-0.092914
              159.647	-0.057487  -0.076203	-0.096257
              161.555	-0.063503  -0.082219	-0.103610
              163.145	-0.065508  -0.084893	-0.105615
              165.053	-0.059492  -0.081551	-0.100936
              180.000	0.015374    0.000000	-0.015374
            </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>-1.839</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>-1.122</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <function name="aero/coefficient/Cnbeta">
       <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>0.096</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnp">
        <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-aero-rad_sec</property>
            <value>-0.0109</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>-0.082</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>-0.0502</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>0.0552</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>