<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Fokker 70" version="2.0" release="BETA"
   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: 1.10 $ </version>
  <description> Fokker 70 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"/>
 </fileheader>

<!--
  File:     Fokker-70.xml
  Inputs:
    name:          Fokker-70
    type:          two-engine transonic transport
    max weight:    81011.7 lb
    wing span:     92.13048 ft
    length:        91.47428 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:  80.49 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" >   47.2440 </htailarm>
   <vtailarea unit="FT2">  132.396 </vtailarea>
   <vtailarm  unit="FT" >   37.4015 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 587.73 </x>
     <y>   0.00 </y>
     <z>  38.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>  76.84 </x>
     <y> -30.00 </y>
     <z>  88.94 </z>
   </location>
   <location name="VRP" unit="IN">
     <x> 566.0 </x>
     <y>   0.0 </y>
     <z>  24.4 </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    200203 </ixx>
   <iyy unit="SLUG*FT2">    455983 </iyy>
   <izz unit="SLUG*FT2">    672987 </izz>
   <emptywt unit="LBS" >     49985 </emptywt>
   <location name="CG" unit="IN">
     <x> 605.73 </x>
     <y>   0.00 </y>
     <z>  38.12 </z>
   </location>

   <pointmass name="pilot">
     <weight unit="LBS"> 230 </weight>
     <location name="POINTMASS" unit="IN">
       <x> 96.84 </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> 96.84 </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> 206 </x>
       <y> 30.0 </y>
       <z> 66.0 </z>
     </location>
   </pointmass>

 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 142.70 </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">      15500.51 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  3200.17 </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> 627.88 </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">      81011.70 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 16202.34 </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> 627.88 </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">      81011.70 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 16202.34 </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> 603.73 </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">      81011.70 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 16202.34 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 603.73 </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">      81011.70 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 16202.34 </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>  893.52 </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>  893.52 </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>  893.52 </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>  893.52 </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> 601.73 </x>
       <y>-190.59 </y>
       <z>   0.0  </z>
     </location>
     <capacity unit="LBS"> 12144.0 </capacity>
     <contents unit="LBS"> 11740.8 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 601.73 </x>
       <y> 190.59 </y>
       <z>   0.0  </z>
     </location>
     <capacity unit="LBS"> 12144.0 </capacity>
     <contents unit="LBS"> 11740.8 </contents>
  </tank>
<!--
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 603.73 </x>
       <y>   0.00 </y>
       <z> -27.44 </z>
     </location>
     <capacity unit="LBS"> 1174.08 </capacity>
     <contents unit="LBS"> 587.04 </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>

        <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/cl-squared</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/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</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> 0.5017 </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/CLalpha">
                <description>Lift_due_to_alpha</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> 10.3399 </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> 3.9655 </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>
                    <property>fcs/left-aileron-pos-rad</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/function/kCmge">
                <description>Change_in_lift_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>

            <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>-3.3520</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	-3.3407
                              2.0000	-0.8352
                          </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>-56.2586</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>-21.5757</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>0.1205</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  -0.1277
                        12203256  -0.0092
                        16640803  -0.0041
                        22178898  -0.0023
                     </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>-0.1087</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>-0.0756</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>
