<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F-104C" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Aeromatic v 0.91 </author>
  <filecreationdate>2009-08-14</filecreationdate>
  <version>$Revision: 1.25 $</version>
  <description>Models an F-104C</description>
      <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:     F-104C-jsbsim.xml
  Inputs:
    name:          F-104C
    type:          single-engine transonic/supersonic fighter
    max weight:    27855 lb
    wing span:     21.94 ft
    length:        54.77 ft
    wing area:     196.1 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     1
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  105 lb/sq-ft
    CL-alpha:      3.5 per radian
    CL-0:          0.08
    CL-max:        1
    CD-0:          0.021
    K:             0.12

-->

<!--
  Note:
  All tables that contain data due to Mach 0.257 and 1.8 are taken from Roskam
-->

 <metrics>
   <wingarea  unit="FT2">196.10</wingarea>
   <wingspan  unit="FT" >21.94</wingspan>
   <wing_incidence>0</wing_incidence>
   <chord     unit="FT" >9.55</chord>
   <htailarea unit="FT2">48.20</htailarea>
   <htailarm  unit="FT" > 46.86</htailarm>
   <vtailarea unit="FT2">43.70</vtailarea>
   <vtailarm  unit="FT" >23.23</vtailarm>
   <location name="AERORP" unit="IN">
     <x>319.5</x>
     <y>0.0</y>
     <z>-35.08</z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>143</x>
     <y>0.0</y>
     <z>-4.25</z>
   </location>
   <location name="VRP" unit="IN">
     <x>319.5</x>
     <y>0.0</y>
     <z>-35.08</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">3663</ixx>
   <iyy unit="SLUG*FT2">59000</iyy>		<!-- orig: 38362, Rk: 59000 -->
   <izz unit="SLUG*FT2">60000</izz>		<!-- orig: 24572, Rk: 60000 -->
   <ixy unit="SLUG*FT2">0</ixy>
   <ixz unit="SLUG*FT2">0</ixz>
   <iyz unit="SLUG*FT2">0</iyz>
   <emptywt unit="LBS" >12760</emptywt>
   <location name="CG" unit="IN">
     <x>319.5</x>
     <y>0.0</y>
     <z>-35.08</z>
   </location>

   <pointmass name="left-tip-tank"><!--empty-->
      <weight unit="LBS">125</weight>
      <location name="POINTMASS" unit="IN">
          <x>389</x>
          <y>-148</y>
          <z>-52</z>
      </location>
   </pointmass>

   <pointmass name="right-tip-tank"><!--empty-->
      <weight unit="LBS">125</weight>
      <location name="POINTMASS" unit="IN">
          <x>389</x>
          <y>148</y>
          <z>-52</z>
      </location>
   </pointmass>

 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x>213</x>
     <y>0.0</y>
     <z>-132</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">       6723.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  2241.00 </damping_coeff>
   <max_steer unit="DEG">60.00</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>393.6</x>
     <y>-63.20</y>
     <z>-121</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">      22410.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  4482.00 </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>393.6</x>
     <y>63.20</y>
     <z>-121</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">      22410.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  4482.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="STRUCTURE" name="NOSE">
    <location unit="IN">
     <x>0</x>
     <y>0</y>
     <z>-43</z>
    </location>
    <static_friction>0.80</static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      22410.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  4482.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="TAIL">
    <location unit="IN">
     <x>656</x>
     <y>0</y>
     <z>-2.5</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      22410.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  4482.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x>422.4</x>
     <y>-166.5</y>
     <z>-54.6</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      22410.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  4482.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x>422.4</x>
     <y>166.5</y>
     <z>-54.6</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      22410.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  4482.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="J79-GE-11A">
    <location unit="IN">
      <x>342.06</x>
      <y>0.00</y>
      <z>-23.29</z>
    </location>
    <orient unit="DEG">
      <pitch>0.0</pitch>
      <roll>0.0</roll>
      <yaw>0.0</yaw>
    </orient>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <thruster file="direct">
     <location unit="IN">
       <x>622.05</x>
       <y>0.00</y>
       <z>-23.29</z>
     </location>
     <orient unit="DEG">
       <pitch>0.0</pitch>
       <roll>0.0</roll>
       <yaw>0.0</yaw>
     </orient>
    </thruster>
  </engine>

<!--internal-->

  <tank type="FUEL" number="0">
     <location unit="IN">
     <x>319.5</x>
     <y>0.0</y>
     <z>-35.08</z>
     </location>
     <capacity unit="LBS">6050.00</capacity>
     <contents unit="LBS">5000.00</contents>
  </tank>

<!--left tip tank-->

  <tank type="FUEL" number="1">
     <location unit="IN">
     <x>389</x>
     <y>-148</y>
     <z>-52</z>
     </location>
     <capacity unit="LBS">1400.00</capacity>
     <contents unit="LBS">1000.00</contents>
  </tank>

<!--right tip tank-->

  <tank type="FUEL" number="2">
     <location unit="IN">
     <x>389</x>
     <y>148</y>
     <z>-52</z>
     </location>
     <capacity unit="LBS">1400.00</capacity>
     <contents unit="LBS">1000.00</contents>
  </tank>

 </propulsion>

 <system file="armament"/>
 <system file="beacon"/>
 <system file="BLC"/>
 <system file="canopy"/>
 <system file="chute"/>
 <system file="crash-detect"/>
 <system file="FCS-pitch"/>
 <system file="FCS-roll"/>
 <system file="FCS-yaw"/>
 <system file="flaps"/>
 <system file="gear"/>
 <system file="NWS"/>
 <system file="radar"/>
 <system file="speedbrakes"/>
 <system file="tailhook"/>

 <flight_control name="FCS"></flight_control>

 <aerodynamics>

 <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    1.2290
           0.1000    1.1240
           0.1500    1.1160
           0.2000    1.1240
           0.3000    1.1050
           0.4000    1.0410
           0.5000    1.0340
           0.6000    1.0190
           0.7000    1.0080
           0.8000    1.0030
           0.9000    1.0010
           1.0000    1.0000
           1.1000    1.0000
         </tableData>
      </table>
   </product>
 </function>

  <axis name="LIFT">

     <function name="aero/coefficient/CLo">
        <description>Lift_at_zero_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.4000  0.0100
                0.6000  0.0100
                0.8000  0.0100
                0.9000  0.0100
                1.0000  -0.0100
                1.2000  -0.0200
                1.4000  0.0400
                1.6000  0.0320
                1.8000  0.0200
                2.0000  0.0100
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CLalpha">
        <description>Lift_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/alpha-rad</property>
          <property>velocities/mach</property>
          <property>aero/function/kCLge</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.4000  7.1154
                0.6000  4.8432
                0.8000  4.2637
                0.9000  4.3529
                1.0000  4.2055
                1.2000  3.1401
                1.4000  2.2916
                1.6000  1.7603
                1.8000  1.3831
                2.0000  1.1042
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CLDf">
        <description>Delta_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">velocities/mach</independentVar>
              <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
              <tableData>
                        0.0000  7.0000  13.0000
                0.6500  0.0000  0.0890  0.4000
                0.7000  0.0000  0.0890  0.3810
                0.7500  0.0000  0.0990  0.3410
                0.8000  0.0000  0.1080  0.3520
                0.8500  0.0000  0.1280  0.3460
                0.9000  0.0000  0.1380  0.1390
                0.9500  0.0000  0.1280  0.2900
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CLDh">
        <description>Lift_due_to_Horizontal_tail_Deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/elevator-pos-rad</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  0.6800
                1.8000  0.5200
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CLq">
        <description>Lift_due_to_pitch_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>velocities/q-aero-rad_sec</property>
          <property>aero/ci2vel</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  2.3000
                1.8000  1.9000
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CLadot">
        <description>Lift_due_to_alpha_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/alphadot-rad_sec</property>
          <property>aero/ci2vel</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  0.6600
                1.8000  0.8200
              </tableData>
            </table>
        </product>
      </function>

    <function name="aero/coefficient/dCLslat">
       <description>Delta_Lift_due_to_slats</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
		<table>
			<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
			<tableData>
				0.00  0.025
				0.30  0.125
				1.00  0.25
			</tableData>
		</table>
       </product>
    </function>

    <function name="aero/coefficient/CLBLC">
       <description>Delta_Lift_due_to_BLC</description>
       <product>
           <property>systems/BLC/active</property>
           <value> 0.2 </value>
       </product>
    </function>

    <function name="aero/coefficient/dCLsb">
       <description>Delta_Lift_due_to_speedbrake</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

      <function name="aero/coefficient/CDo">
        <description>Drag_at_zero_lift</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.0000  0.0160
                0.8000  0.0160
                0.8500  0.0163
                0.8800  0.0170
                0.9000  0.0170
                0.9250  0.0190
                0.9500  0.0230
                0.9750  0.0310
                1.0000  0.0380
                1.0500  0.0470
                1.1000  0.0500
                1.1500  0.0500
                1.2000  0.0490
                1.4000  0.0468
                1.6000  0.0440
                1.8000  0.0430
                2.0000  0.0422
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CDalpha">
        <description>Drag_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
            <table>
              <independentVar lookup="row">aero/alpha-rad</independentVar>
              <independentVar lookup="column">velocities/mach</independentVar>
              <tableData>
                        0.0000  0.8000  0.9000  1.0000  1.2000  1.4000  1.6000  1.8000  2.0000
                -0.0700 0.0034  0.0049  0.0059  0.0093  0.0109  0.0040  0.0035  0.0042  0.0041
                -0.0350 0.0010  0.0013  0.0015  0.0026  0.0032  0.0010  0.0011  0.0017  0.0018
                0.0000  0.0002  0.0002  0.0001  0.0002  0.0006  0.0011  0.0010  0.0008  0.0004
                0.0350  0.0024  0.0022  0.0031  0.0036  0.0046  0.0072  0.0059  0.0052  0.0037
                0.0700  0.0093  0.0118  0.0165  0.0195  0.0187  0.0243  0.0198  0.0161  0.0133
                0.1050  0.0240  0.0332  0.0465  0.0472  0.0425  0.0506  0.0430  0.0345  0.0176
                0.1400  0.0465  0.0589  0.0822  0.0860  0.0788  0.0837  0.0722  0.0593  0.0479
                0.1750  0.0703  0.0851  0.1361  0.1674  0.1298  0.1257  0.1052  0.0894  0.0741
                0.2090  0.1074  0.1205  0.1988  0.3273  0.2195  0.1945  0.1487  0.1220  0.1013
                0.2440  0.1679  0.1684  0.2999  0.6122  0.3791  0.3195  0.1529  0.1650  0.1331
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CDbeta">
       <description>Drag_due_to_sideslip</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57    1.230
              -0.26    0.050
               0.00    0.000
               0.26    0.050
               1.57    1.230
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDdh">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.04</value>
       </product>
    </function>

    <function name="aero/coefficient/CDgear">
        <description>Drag_due_to_landing_gear</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
            <table>
              <independentVar>gear/gear-pos-norm</independentVar>
              <tableData>
                0.0000  0.0000
                0.3000  0.1000
                1.0000  0.0600
              </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>
		<value>0.002679</value>
	</product>
</function>

<function name="aero/coefficient/CDslat">
	<description>Drag_due_to_slats</description>
	<product>
		<property>aero/qbar-psf</property>
		<property>metrics/Sw-sqft</property>
		<table>
			<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
			<tableData>
				0.00  0.003
				0.30  0.015
				1.00  0.03
			</tableData>
		</table>
	</product>
</function>

    <function name="aero/coefficient/CDbc">
       <description>Drag_due_to_braking_chute</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>systems/chute/unfurl-norm</property>
           <value>.75</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>0.04</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>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -1.1800
                1.8000  -1.0450
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CYDr">
        <description>Side_force_due_to_rudder</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/rudder-pos-rad</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  0.3290
                1.8000  0.0870
              </tableData>
            </table>
        </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>velocities/mach</independentVar>
              <tableData>
                0.2570  -0.1750
                1.8000  -0.0930
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/Clp">
        <description>Roll_moment_due_to_roll_rate_(roll_damping)</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>velocities/mach</independentVar>
              <tableData>
                0.2570  -0.2850
                1.8000  -0.2720
              </tableData>
            </table>
        </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-rad_sec</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  0.2650
                1.8000  0.1540
              </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>velocities/mach</independentVar>
              <tableData>
                0.2570  0.0392
                1.8000  0.0173
              </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>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  0.0448
                1.8000  0.0079
              </tableData>
            </table>
        </product>
      </function>

  </axis>

  <axis name="PITCH">

      <function name="aero/coefficient/Cmalpha">
        <description>Pitch_moment_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/alpha-rad</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -0.6440
                1.8000  -1.3080
              </tableData>
            </table>
        </product>
      </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>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570   0.0300
                1.8000  -0.0280
              </tableData>
            </table>
        </product>
      </function>

    <function name="aero/coefficient/Cmde">
       <description>Pitch_moment_due_to_elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -0.800
              2.0     -0.200
            </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-rad_sec</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -5.84
                1.8000  -4.83
              </tableData>
            </table>
        </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>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -1.6400
                1.8000  -2.0500
              </tableData>
            </table>
        </product>
      </function>

  </axis>

  <axis name="YAW">

    <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>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  0.5070
                1.8000  0.2420
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/Cnp">
        <description>Yaw_moment_due_to_roll_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/p-rad_sec</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -0.1440
                1.8000  -0.0930
              </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-rad_sec</property>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -0.7530
                1.8000  -0.6490
              </tableData>
            </table>
        </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>
            <table>
              <independentVar>velocities/mach</independentVar>
              <tableData>
                0.2570  -0.1645
                1.8000  -0.0435
              </tableData>
            </table>
        </product>
      </function>

      <function name="aero/coefficient/CnDa">
        <description>Yaw_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>velocities/mach</independentVar>
              <tableData>
                0.2570  0.0042
                1.8000  0.0025
              </tableData>
            </table>
        </product>
      </function>
  </axis>

 </aerodynamics>

</fdm_config>
