<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Fokker-100" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Erik Hofman </author>
  <filecreationdate>2010-08-08</filecreationdate>
  <version>$Revision: 1.31 $</version>
  <description> Fokker-100 commercial airliner </description>
  <reference title="Butterworth-Heinemann - Civil Jet Aircraft Design (BH)
        http://www.elsevierdirect.com/companions/9780340741528/appendices/data-a/table-8/table.htm"/>
  <reference title="Lissys - PIANO aircraft analysis software
        http://www.lissys.demon.co.uk/f7tx2.html"/>
  <reference title="Aerodynamic Design of Transport Aircraft
        http://www.scribd.com/doc/23956816/Aerodynamic-Design-of-Transport-Aircraft"/>
      <note>
        This model was created using publicly available data, publicly available
        technical reports, textbooks, and guesses. It contains no proprietary or
        restricted data. If this model has been validated at all, it would be
        only to the extent that it seems to "fly right", and that it possibly
        complies with published, publicly known, performance data (maximum speed,
        endurance, etc.). Thus, this model is meant for educational and entertainment
        purposes only.

        This simulation model is not endorsed by the manufacturer. This model is not
        to be sold.
      </note>
 </fileheader>

<!--
  File:     Fokker-100.xml
  Inputs:
    name:          Fokker-100
    type:          two-engine transonic transport
    max weight:    95013.45 lb
    wing span:     92.13048 ft
    length:        106.6325 ft
    wing area:     1006.5275 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes

  Outputs:
    wing loading:  94.40 lb/sq-ft
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.72
    CD-0:          0.02
    K:             0.043

-->

 <metrics>
   <wingarea  unit="FT2"> 1006.53 </wingarea>
   <wingspan  unit="FT" >   92.13 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   12.4671 </chord>
   <htailarea unit="FT2">  233.792 </htailarea>
   <htailarm  unit="FT" >   52.4934 </htailarm>
   <vtailarea unit="FT2">  132.396 </vtailarea>
   <vtailarm  unit="FT" >   44.6194 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 699.48 </x> <!-- 668.48 -->
     <y>   0.00 </y>
     <z>  38.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 122.04 </x>
     <y> -30.00 </y>
     <z>  88.94 </z>
   </location>
   <location name="VRP" unit="IN">
     <x> 580.0 </x>
     <y>   0.0 </y>
     <z>   0.0 </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    234805 </ixx>
   <iyy unit="SLUG*FT2">    726720 </iyy>
   <izz unit="SLUG*FT2">    925012 </izz>
   <emptywt unit="LBS" >     54217 </emptywt>
   <location name="CG" unit="IN">
     <x> 719.81 </x> <!-- 693.81 -->
     <y>   0.00 </y>
     <z>  38.12 </z>
   </location>
   <pointmass name="pilot">
     <weight unit="LBS"> 230 </weight>
     <location name="POINTMASS" unit="IN">
       <x> 122.04 </x>
       <y> -30.0 </y>
       <z>  66.0 </z>
     </location>
   </pointmass>
   <pointmass name="copilot">
     <weight unit="LBS"> 230 </weight>
     <location name="POINTMASS" unit="IN">
       <x> 122.04 </x>
       <y>  30.0 </y>
       <z>  66.0 </z>
     </location>
   </pointmass>
   <pointmass name="steward">
     <weight unit="LBS"> 400 </weight>
     <location name="POINTMASS" unit="IN">
       <x>  218 </x>
       <y>  32.0 </y>
       <z>  66.0 </z>
     </location>
   </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 172.87 </x>
     <y>   0.00 </y>
     <z> -55.73 </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">      15500.03 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  3200.34 </damping_coeff>
   <max_steer unit="DEG"> 76.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 731.93 </x>
     <y>-101.65 </y>
     <z> -63.53 </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">      95013.45 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 19002.69 </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> 731.93 </x>
     <y> 101.65 </y>
     <z> -63.53 </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">      95013.45 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 753.77 </x>
     <y>-1105.4 </y>
     <z>   0.0 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      95013.45 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 753.77 </x>
     <y> 1105.4 </y>
     <z>   0.0  </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      95013.45 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
 </contact>

 </ground_reactions>

 <external_reactions>
    <force name="pushback" frame="BODY">
       <location unit="IN">
          <x>-139</x>
          <y>0</y>
          <z>-71</z>
       </location>
       <direction>
          <x>1</x>
          <y>0</y>
          <z>0</z>
       </direction>
    </force>
 </external_reactions>

 <propulsion>

   <engine file="Tay-620">
    <location unit="IN">
      <x>  922.52 </x>
      <y> -101.65 </y>
      <z>   43.53 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN">
       <x>  922.52 </x>
       <y> -101.65 </y>
       <z>   43.53 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="Tay-620">
    <location unit="IN">
      <x>  922.52 </x>
      <y>  101.65 </y>
      <z>   43.53 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <thruster file="direct">
     <location unit="IN">
       <x>  922.52 </x>
       <y>  101.65 </y>
       <z>   43.53 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>  0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> 713.81 </x>
       <y>-190.59 </y>
       <z>   0.0  </z>
     </location>
     <capacity unit="LBS"> 13360.01 </capacity>
     <contents unit="LBS">  8688.50 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 713.81 </x>
       <y> 190.59 </y>
       <z>   0.0  </z>
     </location>
     <capacity unit="LBS"> 13360.01 </capacity>
     <contents unit="LBS">  8688.50 </contents>
  </tank>
<!--
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 703.77 </x>
       <y>   0.00 </y>
       <z> -31.99 </z>
     </location>
     <capacity unit="LBS"> 1377.01 </capacity>
     <contents unit="LBS"> 688.50 </contents>
  </tank>
-->
 </propulsion>

 <system file="FCS-pitch"/>
 <system file="FCS-roll"/>
 <system file="FCS-yaw"/>
 <system file="flaps"/>
 <system file="gear"/>
 <system file="NWS"/>
 <system file="speedbrakes"/>
 <system file="spoilers.xml"/>
 <system file="pushback"/>

 <flight_control name="FCS: Fokker-100"/>

    <aerodynamics>  

        <function name="aero/function/kCDge">
            <description>Change_in_drag_due_to_ground_effect</description>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	0.0350
                          0.1000	0.4170
                          0.1500	0.5390
                          0.2000	0.6240
                          0.3000	0.7510
                          0.4000	0.8000
                          0.5000	0.8960
                          0.6000	0.9390
                          0.7000	0.9740
                          0.8000	0.9810
                          0.9000	0.9900
                          1.0000	0.9940
                          1.1000	1.0000
                      </tableData>
                  </table>
        </function>

        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	1.3910
                          0.1000	1.2350
                          0.1500	1.1670
                          0.2000	1.1350
                          0.3000	1.0850
                          0.4000	1.1020
                          0.5000	1.0350
                          0.6000	1.0240
                          0.7000	1.0150
                          0.8000	1.0110
                          0.9000	1.0060
                          1.0000	1.0040
                          1.1000	1.0000
                      </tableData>
                  </table>
        </function>

        <function name="aero/function/kCmge">
            <description>Change_in_pitch_due_to_ground_effect</description>
                <table>
                    <independentVar>aero/h_b-mac-ft</independentVar>
                    <tableData>
                          0.0000	1.2030
                          0.1000	1.1270
                          0.1500	1.0900
                          0.2000	1.0730
                          0.3000	1.0460
                          0.4000	1.0550
                          0.5000	1.0190
                          0.6000	1.0130
                          0.7000	1.0080
                          0.8000	1.0060
                          0.9000	1.0030
                          1.0000	1.0020
                          1.1000	1.0000
                    </tableData>
                </table>
        </function>


        <axis name="DRAG">
            <function name="aero/force/Drag_minimum">
               <description>Minimum drag</description>
               <product>
                  <property>aero/qbar-psf</property>
                  <property>metrics/Sw-sqft</property>
                  <value> 0.01922 </value>
               </product>
            </function>
            <function name="aero/coefficient/CDalpha">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                             -1.5700	1.5000
                             -0.2600	0.0422
                              0.0000	0.0000
                              0.2600	0.0422
                              1.5700	1.5000
                          </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/function/kCDge</property>
                    <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.458     0.04432
                              0.546	0.02207
                              0.600	0.01469
                              0.720	0.00867
                              0.800	0.00478
                              0.860	0.00358
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDDflap">
                <description>Drag_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCDge</property>
                    <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                     0.000  25.0   42.0
                              -0.07  0.0000 0.0047 0.0156
                               0.00  0.0000 0.0070 0.0200
                               0.03  0.0001 0.0077 0.0225
                               0.07  0.0005 0.0089 0.0257
                               0.10  0.0008 0.0129 0.0276
                               0.14  0.0025 0.0156 0.0313
                          </tableData>
                      </table>
                </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>velocities/mach</independentVar>
                          <tableData>
                              0.000	0.00000
                              0.600	0.00000
                              0.650	0.00026
                              0.720	0.00115
                              0.770	0.00251
                              0.800	0.00373
                              0.848	0.01067
                              0.860	0.01858
                              1.000	0.02737
                              1.100	0.0390
                              1.800	0.0150
                          </tableData>
                      </table>
                </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>0.0120</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>0.1200</value>
                </product>
            </function>
            <function name="aero/coefficient/CDsp">
                <description>Drag_due_to_spoilers</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/spoiler-pos-norm</property>
                    <value>0.0280</value>
                </product>
            </function>
            <function name="aero/coefficient/CDrv">
                <description>Drag_due_to_reverse</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>propulsion/engine[0]/reverser-angle-rad</property>
                    <property>propulsion/engine[1]/reverser-angle-rad</property>
                    <value>0.0187</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>aero/beta-rad</independentVar>
                          <tableData>
                             -1.5700	1.2300
                             -0.2600	0.0500
                              0.0000	0.0000
                              0.2600	0.0500
                              1.5700	1.2300
                          </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>0.0590</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>-0.6142</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>
                         11093869   0.3126
                         12203256   0.0226
                         16640803   0.0100
                         22178898   0.0057
                      </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> 0.6028 </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> 0.1850 </value>
                </product>
             </function>
        </axis>

        <axis name="LIFT">
            <function name="aero/coefficient/CLflaps">
                <description>Lift_due_to_flap_deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar lookup="row">aero/alpha-rad</independentVar>
                          <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
                          <tableData>
                                     0.000  25.0    42.0 
                              -1.57  0.0000  0.0000  0.0000
                              -1.22 -0.5128 -0.5128 -0.5128
                              -1.05 -0.6908 -0.6908 -0.6908
                              -0.88 -0.7977 -0.7977 -0.7977
                              -0.66 -0.5520 -0.5520 -0.5520
                              -0.31 -1.3801 -0.707  -0.707 
                               0.00  0.217   0.837   1.269
                               0.17  1.109   1.701   2.173
                               0.21  1.270   1.827   2.308
                               0.24  1.400   1.722   1.908
                               0.28  1.336   0.707    0.707
                               0.60  0.8568  0.8568  0.8568
                               0.88  1.2023  1.2023  1.2023
                               1.05  1.0412  1.0412  1.0412
                               1.22  0.7728  0.7728  0.7728
                               1.57  0.0000  0.0000  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> 11.9268 </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>
                 <value> 4.5740 </value>
              </product>
            </function>
            <function name="aero/coefficient/dCLsp">
                <description>Delta_Lift_due_to_spoiler</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/spoiler-pos-norm</property>
                    <property>aero/function/kCLge</property>
                    <value>-0.1200</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>0.6230</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>
                    <table>
                      <independentVar lookup="row">aero/alpha-rad</independentVar>
                      <independentVar lookup="column">aero/Re</independentVar>
                      <tableData>
                                  11093869 12203256 16640803 22178898
                          -0.0349  -0.1993  -0.0655  -0.0606  -0.0605
                           0.3491  -1.3379  -0.2091  -0.2195  -0.2543
                      </tableData>
                    </table>
                </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> -0.3346 </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>
                    <table>
                      <independentVar lookup="row">aero/alpha-rad</independentVar>
                      <independentVar lookup="column">aero/Re</independentVar>
                      <tableData>
                                  11093869 12203256 16640803 22178898
                          -0.0349   0.0237   0.0237   0.0237   0.0237
                           0.3491   4.2068   0.5410   0.5410   0.5410
                      </tableData>
                    </table>
                </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>
                    <table>
                          <independentVar lookup="row">velocities/mach</independentVar>
                          <independentVar lookup="column">fcs/left-aileron-pos-rad</independentVar>
                          <tableData>
                                    -0.349 -0.1745 0.000  0.1745 0.349
                               0.00 -0.043 -0.022  0.000  0.022  0.043
                               0.60 -0.043 -0.022  0.000  0.022  0.043
                               0.65 -0.037 -0.022  0.000  0.022  0.037
                               0.70 -0.027 -0.022  0.000  0.023  0.027
                               0.75 -0.027 -0.019  0.000  0.019  0.027
                               0.88 -0.026 -0.019  0.000  0.019  0.026
                          </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>0.0100</value>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/Cmo">
                <description>Pitching_moment_at_zero_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/function/kCmge</property>
                    <value>-0.000737</value>
                </product>
            </function>
            <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>-3.8664</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>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-3.8610
                              2.0000	-0.9652
                          </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>-74.8519</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>-28.7064</value>
                </product>
            </function>
        </axis>

        <axis name="YAW">
            <!-- Stall initiator -->
            <function name="aero/moment/Yaw_alpha">
               <description>Yaw moment due to alpha</description>
               <product>
                   <property>aero/qbar-psf</property>
                   <property>metrics/Sw-sqft</property>
                   <property>metrics/bw-ft</property>
                   <property>aero/alpha-rad</property>
                   <property>fcs/gear-no-wow</property>
                   <table>
                     <independentVar lookup="row">aero/beta-rad</independentVar>
                     <independentVar lookup="column">aero/Re</independentVar>
                     <tableData>
                                 11093869 12203256
                         -0.3491  -1.0000   0.0000
                          0.3491   1.0000   0.0000
                     </tableData>
                   </table>
               </product>
            </function>
            <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>0.1448</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>
                        11093869  -0.1534
                        12203256  -0.0111
                        16640803  -0.0049
                        22178898  -0.0028
                     </tableData>
                   </table>
               </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>-0.1524</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>-0.0908</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>0.0000</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
</fdm_config>
