fokker130.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Fokker-130" 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> 29 Jan 2016 </filecreationdate>
  <version>$Revision: 1.10 $</version>
  <description> Fokker-130NG 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 130.xml
  Inputs:
    name:          Fokker 130
    type:          2 engine transonic transport
    stall speed:   118.79kts
    max weight:    106298.63 lb
    length:        127.95 ft
    wing: 
     span:         95.05 ft
     area:         unspecified
     mean chord:   12.47 ft
     aspect ratio: 8.43:1
     taper ratio:  0.23:1
     incidence:    2.00 degrees
     dihedral:     0.00 degrees
     sweep:        17.45 degrees

    no. engines:   2
    engine type:   Turbine Engine
    engine layout: aft fuselage

    control type:   Conventional with Yaw Damper

    gear type:     tricycle
    steering type: steering
    retractable?:  yes

  Outputs:
    wing loading:  110.00 lb/sq-ft
    payload:       18697.04 lbs
    CL-alpha:      5.42 per radian
    CL-0:          0.42
    CL-max:        2.30
    CD-0:          0.02
    K:             0.04
    Mcrit:         0.57

  Differences to the Fokker-100:
  ==============================
  * The fuselage is 2.3 meters longer increasing the no. passeners up to 138,
    (at 130 tyypical in economic class).

  * The winglets reduce fuel consumption by 2 to 3% for a typical flight.
    - Up to 7% reduction in drag during takeoff.
    - Up to 3% reduction in drag during cruise.

  * New avionics and fly-by-wire system result in 750kg less weight.
  * The fly-by-wire system results in 10% reduction in drag.

  * A 1,500 kg extra payload capacity in critical takeoff conditions is
    realized for operation at high airfields and in high ambient temperatures.

  * The Fokker 130 is powered by the smallest version of the Pratt & Whitney
    Geared Turbofan engines. This engine family is based on the concept of:
    - A reduction gear between the low speed turbine and the fan
    - A very high bypass ratio and a high Overall Pressure Ratio
    - The lowest specific fuel consumption available in a commercial transport
      engine in this class (22% more economical)

-->

 <metrics>
   <wingarea  unit="FT2"> 1025.90 </wingarea>
   <wingspan  unit="FT" >   95.05 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   12.4671 </chord>
   <htailarea unit="FT2">  233.792 </htailarea>
   <htailarm  unit="FT" >   54.070 </htailarm>
   <vtailarea unit="FT2">  132.396 </vtailarea>
   <vtailarm  unit="FT" >   46.416 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 729.21 </x>
     <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> 105.97 </x>
     <y>   0.0  </y>
     <z>   0.0  </z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    254937 </ixx>
   <iyy unit="SLUG*FT2">   1067460 </iyy>
   <izz unit="SLUG*FT2">   1187805 </izz>
   <emptywt unit="LBS" >     58923 </emptywt>
   <location name="CG" unit="IN">
     <x> 733.63 </x>
     <y>   0.00 </y>
     <z>  38.12 </z>
   </location>
   <pointmass name="pilot">
     <weight unit="LBS"> 230 </weight>
     <location name="POINTMASS" unit="IN">
       <x> 125.86 </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> 125.86 </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>  222 </x>
       <y>  32.0 </y>
       <z>  66.0 </z>
     </location>
   </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 176.69 </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">       7750.03 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  1600.34 </damping_coeff>
   <max_steer unit="DEG"> 5.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 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="PW1217G">
    <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="PW1217G">
    <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>
  <tank type="FUEL" number="3">
     <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">  0 </contents>
  </tank>
  <tank type="FUEL" number="4">
     <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"> 0 </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>
            <product>
                  <table> <!-- adjusted fro winglets -->
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	0.0337
                          0.1000	0.4029
                          0.1500	0.5224
                          0.2000	0.6067
                          0.3000	0.7325
                          0.4000	0.7828
                          0.5000	0.8795
                          0.6000	0.9246
                          0.7000	0.9620
                          0.8000	0.9719
                          0.9000	0.9839
                          1.0000	0.9909
                          1.1000	1.0000
                      </tableData>
                  </table>
            </product>
        </function>

        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	1.3910
                          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>
            </product>
        </function>

        <function name="aero/function/kCmge">
            <description>Change_in_pitch_due_to_ground_effect</description>
            <product>
                <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>
            </product>
        </function>


        <axis name="DRAG"> <!-- adjusted for winglets -->
            <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/CD0">
                <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
                          </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>-0.6150</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   0.3130
                         12203256   0.0226
                         16640803   0.0101
                         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> 0.6649 </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> 13.3752 </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> 5.1295 </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>-4.3294</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	-4.3294
                              2.0000	-1.0824
                          </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>-93.9990</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>-36.0495</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>0.1598</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  -0.1692
                        12203256  -0.0122
                        16640803  -0.0054
                        22178898  -0.0031
                     </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>-0.1831</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>-0.1000</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>