<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="C130" version="2.0" release="PRODUCTION"
 xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
 xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author> </author>
        <filecreationdate> 30 March 2006 </filecreationdate>
        <version> 1.01 </version>
        <description> C130 </description>

<!--
  File:     c130.xml
  Inputs:
    name:          c130
    type:          four-engine transonic transport
    max weight:    175032.9 lb
    wing span:     131.24 ft
    length:        95.149 ft
    wing area:     1743.93 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   turboprop
    engine layout: wings
    yaw damper?    no

  Outputs:
    wing loading:  100.37 lb/sq-ft
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.2
    CD-0:          0.017
    K:             0.042

-->

    </fileheader>

    <metrics>
      <wingarea  unit="FT2"> 1743.93 </wingarea>
      <wingspan  unit="FT" >  131.24 </wingspan>
      <wing_incidence>          2.00 </wing_incidence>
      <chord     unit="FT" >   13.29 </chord>
      <htailarea unit="FT2">  435.98 </htailarea>
      <htailarm  unit="FT" >   42.82 </htailarm>
      <vtailarea unit="FT2">  348.79 </vtailarea>
      <vtailarm  unit="FT" >   42.82 </vtailarm>
      <location name="AERORP" unit="IN"> 
        <x> 627.98 </x>
        <y>   0.00 </y>
        <z>   0.00 </z>
      </location>
      <location name="EYEPOINT" unit="IN">
        <x>  79.93 </x>
        <y> -32.00 </y>
        <z>  80.00 </z>
      </location>
      <location name="VRP" unit="IN">
        <x>0</x>
        <y>0</y>
        <z>0</z>
      </location>
    </metrics>

    <mass_balance>
      <ixx unit="SLUG*FT2">   1438095 </ixx>
      <iyy unit="SLUG*FT2">    853339 </iyy>
      <izz unit="SLUG*FT2">   2307817 </izz>
      <ixy unit="SLUG*FT2">         0 </ixy>
      <ixz unit="SLUG*FT2">         0 </ixz>
      <iyz unit="SLUG*FT2">         0 </iyz>
      <emptywt unit="LBS" >    105020 </emptywt>
      <location name="CG" unit="IN">
        <x> 627.98 </x>
        <y>   0.00 </y>
        <z> -28.54 </z>
      </location>
    </mass_balance>

    <ground_reactions>
      <contact type="BOGEY" name="NOSE">
       <location unit="IN">
         <x> 148.43 </x>
         <y>   0.00 </y> 
         <z> -137.01 </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">      52509.87 </spring_coeff>
       <damping_coeff unit="LBS/FT/SEC"> 17503.29 </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> 653.10 </x>
         <y> -141.74 </y>
         <z> -137.01 </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">      175032.90 </spring_coeff>
       <damping_coeff unit="LBS/FT/SEC"> 35006.58 </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> 653.10 </x>
        <y> 141.74 </y>
        <z> -137.01 </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">      175032.90 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 35006.58 </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> 627.98 </x>
        <y> -65.62 </y>
        <z> -28.54 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      175032.90 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 35006.58 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="RIGHT_WING">
      <location unit="IN">
        <x> 627.98 </x>
        <y>  65.62 </y>
        <z> -28.54 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      175032.90 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 35006.58 </damping_coeff>
    </contact>
  </ground_reactions>

  <propulsion>
    <engine file="WrightCyclone-975C18CB1">
        <location unit="IN">
            <x> 681.6 </x>
            <y> -358 </y>                                                             <!-- aeromatic -246 -->
            <z> -40 </z>
        </location>
        <orient unit="DEG">
            <roll> 0.0 </roll>
            <pitch> 0 </pitch>
            <yaw> 0 </yaw>
        </orient>
        <feed>0</feed>
        <feed>4</feed>
        <feed>7</feed>
        <thruster file="HamiltonStd43E60-6901A">
            <location unit="IN">
                <x> 681.6 </x>
                <y> -358 </y>
                <z> -40 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.0 </pitch>
                <yaw> 0.0 </yaw>
            </orient>
        </thruster>
    </engine>
    <engine file="WrightCyclone-975C18CB1">
        <location unit="IN">
            <x> 681.6 </x>
            <y> -168 </y>                                                             <!-- aeromatic -246 -->
            <z> -40 </z>
        </location>
        <orient unit="DEG">
            <roll> 0.0 </roll>
            <pitch> 0 </pitch>
            <yaw> 0 </yaw>
        </orient>
        <feed>1</feed>
        <feed>4</feed>
        <feed>5</feed>
        <feed>8</feed>
        <thruster file="HamiltonStd43E60-6901A">
            <location unit="IN">
                <x> 681.6 </x>
                <y> -168 </y>
                <z> -40 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.0 </pitch>
                <yaw> 0.0 </yaw>
            </orient>
        </thruster>
    </engine>
    <engine file="WrightCyclone-975C18CB1">
        <location unit="IN">
            <x> 681.6 </x>
            <y> 168 </y>
            <z> -40 </z>
        </location>
        <orient unit="DEG">
            <roll> 0.0 </roll>
            <pitch> 0 </pitch>
            <yaw> 0 </yaw>
        </orient>
        <feed>2</feed>
        <feed>4</feed>
        <feed>6</feed>
        <feed>9</feed>
        <thruster file="HamiltonStd43E60-6901A">
            <location unit="IN">
                <x> 681.6 </x>
                <y> 168 </y>
                <z> -40 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.0 </pitch>
                <yaw> 0.0 </yaw>
            </orient>
        </thruster>
    </engine>
    <engine file="WrightCyclone-975C18CB1">
        <location unit="IN">
            <x> 681.6 </x>
            <y> 358 </y>
            <z> -40 </z>
        </location>
        <orient unit="DEG">
            <roll> 0.0 </roll>
            <pitch> 0 </pitch>
            <yaw> 0 </yaw>
        </orient>
        <feed>3</feed>
        <feed>4</feed>
        <feed>10</feed>
        <thruster file="HamiltonStd43E60-6901A">
            <location unit="IN">
                <x> 681.6 </x>
                <y> 358 </y>
                <z> -40 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0.0 </pitch>
                <yaw> 0.0 </yaw>
            </orient>
        </thruster>
    </engine>

        <tank type="FUEL">    <!-- Tank number 0 --> 
            <documentation>
               1 : middle tank between the engines.
            </documentation>
            <location unit="IN">
                <x> 681.6 </x>
                <y> -280 </y>
                <z> -34.08 </z>
            </location>
            <capacity unit="LBS"> 9330 </capacity>
            <contents unit="LBS"> 9330 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 1 --> 
            <documentation>
               2 and 3 : inboard tanks, at wing root.
            </documentation>
            <location unit="IN">
                <x> 681.6 </x>
                <y> -100 </y>
                <z> -50 </z>
            </location>
            <capacity unit="LBS"> 4740 </capacity>
            <contents unit="LBS"> 4740 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 2 --> 
            <location unit="IN">
                <x> 681.6 </x>
                <y> 100 </y>
                <z> -50 </z>
            </location>
            <capacity unit="LBS"> 4740 </capacity>
            <contents unit="LBS"> 4740 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 3 --> 
            <documentation>
               1 and 4 : middle tank between the engines.
            </documentation>
            <location unit="IN">
                <x> 681.6 </x>
                <y> 280 </y>
                <z> -34.08 </z>
            </location>
            <capacity unit="LBS"> 9330 </capacity>
            <contents unit="LBS"> 9330 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 4 --> 
            <documentation>
               5 : center tank, under the floor.
            </documentation>
            <location unit="IN">
                <x> 681.6 </x>
                <y> 0 </y>
                <z> -90 </z>
            </location>
            <capacity unit="LBS"> 4380 </capacity>
            <contents unit="LBS"> 4380 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 5 --> 
            <documentation>
               2a and 3a : outboard tanks, at wing tip.
            </documentation>
            <location unit="IN">
                <x> 681.6 </x>
                <y> -450 </y>
                <z> -34.08 </z>
            </location>
            <capacity unit="LBS"> 3390 </capacity>
            <contents unit="LBS"> 3390 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 6 --> 
            <location unit="IN">
                <x> 681.6 </x>
                <y> 450 </y>
                <z> -34.08 </z>
            </location>
            <capacity unit="LBS"> 3390 </capacity>
            <contents unit="LBS"> 3390 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 7 --> 
            <documentation>
              emulates cross feed of engine supplies :
              - position like the main engine tank.
              - can feed 1200 gal/h per engine : 1200 x ( 2 / 3600 ) = 0.67 US gal content, if supplied every 2 s from other tanks.
            </documentation>
            <location unit="IN">
                <x> 681.6 </x>
                <y> -280 </y>
                <z> -34.08 </z>
            </location>
            <capacity unit="LBS"> 4.4 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 8 --> 
            <location unit="IN">
                <x> 681.6 </x>
                <y> -100 </y>
                <z> -50 </z>
            </location>
            <capacity unit="LBS"> 4.4 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 9 --> 
            <location unit="IN">
                <x> 681.6 </x>
                <y> 100 </y>
                <z> -50 </z>
            </location>
            <capacity unit="LBS"> 4.4 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>
        <tank type="FUEL">    <!-- Tank number 10 --> 
            <location unit="IN">
                <x> 681.6 </x>
                <y> 280 </y>
                <z> -34.08 </z>
            </location>
            <capacity unit="LBS"> 4.4 </capacity>
            <contents unit="LBS"> 0 </contents>
        </tank>
    </propulsion>
    <flight_control name="c130">
     <channel name="Pitch">

        <summer name="Pitch Trim Sum">
            <input>fcs/elevator-cmd-norm</input>
            <input>fcs/pitch-trim-cmd-norm</input>
            <clipto>
                <min>-1</min>
                <max>1</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Elevator Control">
            <input>fcs/pitch-trim-sum</input>
            <gain>0.01745</gain>
            <range>
                <documentation>
                   replaced -0.35/0.35 by -6/16 deg real.
                </documentation>
                <min>-6</min>
                <max>16</max>
            </range>
            <output>fcs/elevator-pos-rad</output>
        </aerosurface_scale>
        <aerosurface_scale name="Elevator Position Normalizer">
            <input>fcs/pitch-trim-sum</input>
            <range>
                <min>-1</min>
                <max>1</max>
            </range>
            <output>fcs/elevator-pos-norm</output>
        </aerosurface_scale>

     </channel>
     <channel name="Roll">

        <summer name="Roll Trim Sum">
            <input>fcs/aileron-cmd-norm</input>
            <input>fcs/roll-trim-cmd-norm</input>
            <clipto>
                <min>-1</min>
                <max>1</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Left Aileron Control">
            <input>fcs/roll-trim-sum</input>
            <gain>0.01745</gain>
            <range>
                <documentation>
                    replaced -0.35/0.35 by -10/25 deg real.
                </documentation>
                <min>-10</min>
                <max>25</max>
            </range>
            <output>fcs/left-aileron-pos-rad</output>
        </aerosurface_scale>
        <aerosurface_scale name="Left Aileron Position Normalizer">
            <input>fcs/roll-trim-sum</input>
            <range>
                <min>-1</min>
                <max>1</max>
            </range>
            <output>fcs/left-aileron-pos-norm</output>
        </aerosurface_scale>

        <aerosurface_scale name="Right Aileron Control">
            <input>-fcs/roll-trim-sum</input>
            <gain>0.01745</gain>
            <range>
                <documentation>
                    replaced -0.35/0.35 by -10/25 deg real.
                </documentation>
                <min>-10</min>
                <max>25</max>
            </range>
            <output>fcs/right-aileron-pos-rad</output>
        </aerosurface_scale>
        <aerosurface_scale name="Right Aileron Position Normalizer">
            <input>fcs/roll-trim-sum</input>
            <range>
                <min>-1</min>
                <max>1</max>
            </range>
            <output>fcs/right-aileron-pos-norm</output>
        </aerosurface_scale>

     </channel>
     <channel name="Yaw">

        <summer name="Rudder Command Sum">
            <input>fcs/rudder-cmd-norm</input>
            <input>fcs/yaw-trim-cmd-norm</input>
            <clipto>
                <min>-1</min>
                <max>1</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Rudder Control">
            <input>fcs/rudder-command-sum</input>
            <gain>0.01745</gain>
            <range>
                <documentation>
                    replaced -0.35/0.35 by -30/30 deg real.
                </documentation>
                <min>-30</min>
                <max>30</max>
            </range>
            <output>fcs/rudder-pos-rad</output>
        </aerosurface_scale>
        <aerosurface_scale name="Rudder Position Normalizer">
            <input>fcs/rudder-command-sum</input>
            <range>
                <min>-1</min>
                <max>1</max>
            </range>
            <output>fcs/rudder-pos-norm</output>
        </aerosurface_scale>

     </channel>
     <channel name="Aeromechanical">

        <kinematic name="Flaps Control">
            <input>fcs/flap-cmd-norm</input>
            <traverse>
                <documentation>
                  - replaced 30 deg by 41 deg real.
                  - add the 10 deg detent, because of the initial translation (Fowler flap).
                  - add the 35 deg detent, because 60 %, 66 %, 80 % and 100 %.
                </documentation>
                <setting>
                    <position>0</position>
                    <time>0</time>
                </setting>
                <setting>
                    <position>10</position>
                    <time>5</time>
                </setting>
                <setting>
                    <position>27</position>
                    <time>4</time>
                </setting>
                <setting>
                    <position>35</position>
                    <time>4</time>
                </setting>
                <setting>
                    <position>41</position>
                    <time>3</time>
                </setting>
            </traverse>
            <output>fcs/flap-pos-deg</output>
        </kinematic>
        <aerosurface_scale name="Flap Position Normalizer">
          <input>fcs/flap-pos-deg</input>
          <domain>
            <min>0</min>
            <max>41</max>
          </domain>
          <range>
            <min>0</min>
            <max>1</max>
          </range>
          <output>fcs/flap-pos-norm</output>
        </aerosurface_scale>

        <kinematic name="Gear Control">
            <input>gear/gear-cmd-norm</input>
            <traverse>
                <setting>
                    <position>0</position>
                    <time>0</time>
                </setting>
                <setting>
                    <position>1</position>
                    <time>5</time>
                </setting>
            </traverse>
            <output>gear/gear-pos-norm</output>
        </kinematic>

        <kinematic name="Speedbrake Control">
            <input>fcs/speedbrake-cmd-norm</input>
            <traverse>
                <setting>
                    <position>0</position>
                    <time>0</time>
                </setting>
                <setting>
                    <position>1</position>
                    <time>1</time>
                </setting>
            </traverse>
            <output>fcs/speedbrake-pos-norm</output>
        </kinematic>
     </channel>
    </flight_control>
    <aerodynamics>
        <documentation>
            created to smooth takeoff roll.
        </documentation>
        <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	1.2000	
                          0.1000	1.1500	
                          0.1500	1.0900	
                          0.2000	1.0200	
                          1.1000	1.0000	
                      </tableData>
                  </table>
            </product>
        </function>

        <axis name="DRAG">
            <documentation>
               added.
            </documentation>
            <function name="aero/coefficient/CDo">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <value>0.0211</value>
                </product>
            </function>
            <documentation>
              - renamed from CDo.
              - substracted Cdo 0.0211.
            </documentation>
            <function name="aero/coefficient/CDalpha">
                <description>Drag_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -1.5700	1.4789	
                              -0.2600	0.0289	
                              0.0000	0.0039	
                              0.2600	0.0289	
                              1.5700	1.4789	
                          </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>
                    <value>0.0390</value>
                </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>
                              0.0000	0.0000	
                              0.7000	0.0000	
                              1.1000	0.0230	
                              1.8000	0.0150	
                          </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-cmd-norm</property>
                    <value>0.0350</value>
                </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>0.0230</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>0.0250</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>
                              -1.5000	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/elevator-pos-norm</property>
                    <value>0.0350</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>-1.0000</value>
                </product>
            </function>
        </axis>

        <axis name="LIFT">
            <documentation>
               created.
            </documentation>
            <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>
                    <value>0.2400</value>
                </product>
            </function>
            <documentation>
               substracted CLo 0.240.
            </documentation>
            <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>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.2000	-0.5000	                                     <!-- aeromatic -0.740 -->
                              0.0000	0.0000	                                     <!-- aeromatic  0.240 -->
                              0.2400	1.1600	                                     <!-- aeromatic  1.400 -->
                              0.6000	0.4640	                                     <!-- aeromatic  0.704 -->
                          </tableData>
                      </table>
                </product>
            </function>
            <documentation>
              to respect the speed limits of gear and flaps, controls by flap angle,
              to get more lift at takeoff setting.

              old : aero/qbar-psf|metrics/Sw-sqft|fcs/flap-pos-norm
            </documentation>
            <function name="aero/coefficient/dCLflap">
                <description>Delta_Lift_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/function/kCLge</property>
                      <table>
                          <independentVar>fcs/flap-pos-deg</independentVar>
                          <tableData>
                              0.0000	0.0000	
                              10.0000	0.4000	
                              27.0000	0.4600	
                              35.0000	0.5300	
                              41.0000	0.6000	
                          </tableData>
                      </table>
                </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>0.0000</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>0.2000</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>
                    <value>-0.1000</value>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <value>-0.4000</value>
                </product>
            </function>
            <function name="aero/coefficient/Clr">
                <description>Roll_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>0.1500</value>
                </product>
            </function>
            <function name="aero/coefficient/Clda">
                <description>Roll_moment_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1500	
                              2.0000	0.0500	
                          </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/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>-0.4000</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	-1.0000	
                              2.0000	-0.2500	
                          </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>-22.0000</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>-8.0000</value>
                </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>
                    <value>0.1200</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnr">
                <description>Yaw_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>-0.1500</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>-0.0080</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
</fdm_config>
