p51d-jsbsim.xml

<?xml version="1.0"?>

<!--

Modified version of what was originally in FlightGear CVS.  This has 
been extensively modified by:

Hal V. Engel hvengel@astound.net

-->
<!--

Daniel Dubreuil, a few changes on stall and spin departure for takeoff and landing, spiraling propwash effect

-->

<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="P-51D (JSBSim)" version="2.0" release="BETA"
    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

    <fileheader>
        <author> Aeromatic / Jon Berndt / DATCOM / Hal V. Engel</author>
        <filecreationdate> 2001-01-01 </filecreationdate>
        <version> $Revision: 1.16 $ </version>
        <description> Advanced model of P-51D fighter </description>
    </fileheader>

    <metrics>
        <wingarea unit="FT2"> 235 </wingarea>
        <wingspan unit="FT"> 37.1 </wingspan>
        <wing_incidence unit="DEG"> 1.00 </wing_incidence>
        <chord unit="FT"> 6.6 </chord>
        <htailarea unit="FT2"> 41 </htailarea>
        <htailarm unit="FT"> 15 </htailarm>
        <vtailarea unit="FT2"> 20 </vtailarea>
        <vtailarm unit="FT"> 15 </vtailarm>
        <location name="AERORP" unit="IN">
            <x> 99 </x>
            <y> 0 </y>
            <z> -26.5 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 95 </x>
            <y> 0 </y>
            <z> 30 </z>
        </location>
        <location name="VRP" unit="IN">
            <x> 0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <ixx unit="SLUG*FT2"> 8031 </ixx>
        <iyy unit="SLUG*FT2"> 9274 </iyy>
        <izz unit="SLUG*FT2"> 14547 </izz>
        <emptywt unit="LBS"> 7125 </emptywt>
        <location name="CG" unit="IN">
            <x> 98 </x>
            <y> 0 </y>
            <z> -9 </z>
        </location>
        <pointmass name="pilot">
            <weight unit="LBS"> 180 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> 0 </y>
                <z> 15 </z>
            </location>
        </pointmass>

         <!-- each 50 cal bullet is a little less than 180 grams but with links are
      probably close to 180 gram each.  The inner two guns can have up to 400
      rounds each and the outer 4 guns can be loaded with up to 270 rounds each. -->

      <pointmass name="Ammo right inner gun">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 100 </x>
                <y> -79.2</y>
                <z> -19.2 </z>
            </location>
        </pointmass>
        <pointmass name="Ammo left inner gun">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 100 </x>
                <y> 79.2</y>
                <z> -19.2 </z>
            </location>
        </pointmass>

        <pointmass name="Ammo right middle gun">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 100 </x>
                <y> -87.6</y>
                <z> -19.2 </z>
            </location>
        </pointmass>
        <pointmass name="Ammo left middle gun">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 100 </x>
                <y> 87.6</y>
                <z> -19.2 </z>
            </location>
        </pointmass>

        <pointmass name="Ammo right outer gun">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 100 </x>
                <y> -96</y>
                <z> -19.2 </z>
            </location>
        </pointmass>
        <pointmass name="Ammo left outer gun">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 100 </x>
                <y> 96</y>
                <z> -19.2 </z>
            </location>
        </pointmass>

        <pointmass name="left rockets">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> 87.6</y>
                <z> -30 </z>
            </location>
        </pointmass>
        <pointmass name="right rockets">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> -87</y>
                <z> -30 </z>
            </location>
        </pointmass>

        <pointmass name="left bomb">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> 87.6</y>
                <z> -43 </z>
            </location>
        </pointmass>
        <pointmass name="right bomb">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> -87</y>
                <z> -43 </z>
            </location>
        </pointmass>

        <pointmass name="left drop tank">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> 87.6</y>
                <z> -43 </z>
            </location>
        </pointmass>
        <pointmass name="right drop tank">
            <weight unit="LBS"> 0 </weight>
            <location name="POINTMASS" unit="IN">
                <x> 98 </x>
                <y> -87</y>
                <z> -43 </z>
            </location>
        </pointmass>

    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="LEFT_MLG">
            <location unit="IN">
                <x> 75.25 </x>
                <y> -72 </y>
                <z> -85 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 9800 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2500 </damping_coeff>
            <damping_coeff_rebound unit="LBS/FT/SEC">6200</damping_coeff_rebound>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="RIGHT_MLG">
            <location unit="IN">
                <x> 75.25 </x>
                <y> 72 </y>
                <z> -85 </z>
            </location>
            <static_friction> 0.8 </static_friction>
            <dynamic_friction> 0.5 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 9800 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 2500 </damping_coeff>
            <damping_coeff_rebound unit="LBS/FT/SEC">6200</damping_coeff_rebound>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="TAIL_LG">
            <location unit="IN">
                <x> 270.2 </x>
                <y> 0 </y>
                <z> -37.5 </z>
            </location>
            <static_friction> 0.66 </static_friction>
            <dynamic_friction> 0.6 </dynamic_friction>
            <rolling_friction> 0.02 </rolling_friction>
            <spring_coeff unit="LBS/FT"> 3500 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 4280 </damping_coeff>
            <steerability> STEERABLE </steerability>
            <max_steer unit="DEG"> 360.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>1</retractable>
        </contact>
        
        <!-- Next three are jack stands for testing landing gear functionality
         <contact type="STRUCTURE" name="LEFT_WING_TIP_JACK_STAND">
              <location unit="IN">
              <x> 25 </x>
              <y> -222 </y>
              <z>  -97 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

            <contact type="STRUCTURE" name="RIGHT_WING_TIP_JACK_STAND">
              <location unit="IN">
              <x> 25 </x>
              <y> 222 </y>
              <z>  -97 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="TAIL_JACK_STAND">
              <location unit="IN">
              <x> 270 </x>
              <y> 0 </y>
              <z>  -95 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>
          
        Comment out the Jack stand section when not doing gear tests -->

          <contact type="STRUCTURE" name="LEFT_WING_TIP_BOTTOM">
              <location unit="IN">
              <x> 103 </x>
              <y> -217.5 </y>
              <z>  -11.5 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

            <contact type="STRUCTURE" name="RIGHT_WING_TIP_BOTTOM">
              <location unit="IN">
              <x> 103 </x>
              <y> 217.5 </y>
              <z>  -11.5 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>
          
          <contact type="STRUCTURE" name="LEFT_WING_TIP_TOP">
              <location unit="IN">
              <x> 103 </x>
              <y> -217.5 </y>
              <z>  -4.6 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="RIGHT_WING_TIP_TOP">
              <location unit="IN">
              <x> 103 </x>
              <y> 217.5 </y>
              <z>  -4.6 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>
          
          <contact type="STRUCTURE" name="LEFT_WING_TIP_FRONT">
              <location unit="IN">
              <x> 84 </x>
              <y> -222.5 </y>
              <z>  -4.6 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="RIGHT_WING_TIP_FRONT">
              <location unit="IN">
              <x> 84 </x>
              <y> 222.5 </y>
              <z>  -8 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="TAIL_BOTTOM">
              <location unit="IN">
              <x> 327 </x>
              <y> 0 </y>
              <z>  -8.6 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="TAIL_TOP">
              <location unit="IN">
              <x> 318 </x>
              <y> 0 </y>
              <z>  65 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="NOSE_BOTTOM">
              <location unit="IN">
              <x> 0 </x>
              <y> 0 </y>
              <z>  -25 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="NOSE_TOP">
              <location unit="IN">
              <x> 0 </x>
              <y> 0 </y>
              <z> 13 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="CANOPY">
              <location unit="IN">
                <x> 133 </x>
                <y> 0 </y>
                <z> 34 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>
            
           <contact type="STRUCTURE" name="BELLY">
              <location unit="IN">
              <x> 52 </x>
              <y> 0 </y>
              <z>  -34 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>  

           <contact type="STRUCTURE" name="DOG_HOUSE">
              <location unit="IN">
              <x> 143 </x>
              <y> 0 </y>
              <z> -46 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       11000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  1179.23 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="PROP_BOTTOM">
              <location unit="IN">
              <x> -13.6 </x>
              <y> 0 </y>
              <z> -70.4 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       500 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  5000 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="PROP_TOP">
              <location unit="IN">
              <x> -17.7 </x>
              <y> 0 </y>
              <z> 65.1 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       500 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  5000 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="PROP_LEFT">
              <location unit="IN">
              <x> -15.5 </x>
              <y> -67.76 </y>
              <z> -3.4 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       500 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  5000 </damping_coeff>
          </contact>

          <contact type="STRUCTURE" name="PROP_RIGHT">
              <location unit="IN">
              <x> -15.5 </x>
              <y> 67.76 </y>
              <z> -3.4 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       500 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  5000 </damping_coeff>              
          </contact>
          
          <contact type="STRUCTURE" name="PROP_SPINNER">
              <location unit="IN">
              <x> -32.67 </x>
              <y> 0 </y>
              <z> -3.1265 </z>
              </location>
              <static_friction>  0.80 </static_friction>
              <dynamic_friction> 0.50 </dynamic_friction>
              <spring_coeff unit="LBS/FT">       5000 </spring_coeff>
              <damping_coeff unit="LBS/FT/SEC">  5000 </damping_coeff>
         </contact>

    </ground_reactions>

    <propulsion>
        <engine file="Packard-V-1650-7">
            <location unit="IN">
                <x> 36 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <orient unit="DEG">
                <roll> -4.0 </roll>
                <pitch> 2.5 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
            <feed>1</feed>
            <feed>2</feed>
            <feed>3</feed>
            <feed>4</feed>
            <thruster file="P51prop">
                <location unit="IN">
                    <x> 36 </x>
                    <y> 0 </y>
                    <z> 0 </z>
                </location>
                <orient unit="DEG">
                    <roll> -4.0 </roll>
                    <pitch> 2.5 </pitch>
                    <yaw> 0 </yaw>
                </orient>
                <sense> 1 </sense>
                <p_factor> 60 </p_factor>
            </thruster>
        </engine>

        <!--
           internal wing tanks
           capacity 92 US gallons each
        -->           
        <tank type="FUEL" number="0">    <!-- Tank number 0 left wing -->
            <location unit="IN">
                <x> 106 </x>
                <y> -80 </y>
                <z> -9.675 </z>
            </location>
            <capacity unit="LBS"> 553.84 </capacity>
            <contents unit="LBS"> 396 </contents>
            <priority> 1 </priority>
            <type> AVGAS </type> 
        </tank>
        <tank type="FUEL" number="1">    <!-- Tank number 1 right wing-->
            <location unit="IN">
                <x> 106 </x>
                <y> 80 </y>
                <z> -9.675 </z>
            </location>
            <capacity unit="LBS"> 553.84 </capacity>
            <contents unit="LBS"> 396 </contents>
            <priority> 1 </priority>
            <type> AVGAS </type>
        </tank>
        <tank type="FUEL" number="2">    <!-- Tank number 2 FUS-->
            <location unit="IN">
                <x> 160 </x>
                <y> 0 </y>
                <z> -3.0 </z>
            </location>
            <capacity unit="LBS"> 511.7 </capacity>
            <contents unit="LBS"> 0 </contents>
            <priority> 1 </priority>
            <type> AVGAS </type>
        </tank>
        <tank type="FUEL" number="3">    <!-- Tank number 3 left drop -->
            <location unit="IN">
                <x> 97.5 </x>
                <y> -198 </y>
                <z> -25 </z>
            </location>
            <capacity unit="LBS"> 451.5 </capacity>
            <contents unit="LBS"> 0 </contents>
            <priority> 1 </priority>
            <type> AVGAS </type>
        </tank>
        <tank type="FUEL" number="4">    <!-- Tank number 4 right drop -->
            <location unit="IN">
                <x> 97.5 </x>
                <y> 198 </y>
                <z> -25 </z>
            </location>
            <capacity unit="LBS"> 451.5 </capacity>
            <contents unit="LBS"> 0 </contents>
            <priority> 1 </priority>
            <type> AVGAS </type>
        </tank>

    </propulsion>

    <system file="propulsion"/>
    <autopilot file="Systems/autothrottle"/>
    <autopilot file="Systems/autocooling"/>
    <system file="mixture-control"/>
    <system file="alpha-buffet"/>
    <system file="crash-detect"/>
    <system file="electrical"/>
    <system file="compressability"/>
    <system file="weapons-weight"/>
    <system file="tail-wheel"/>
    <system file="hydraulic"/>
    <system file="MPAnimation"/>

    <flight_control name="FCS: P51D">

        <channel name="exhaust thrust">

            <switch name="aero/function/running-factor">
                <default value="0.3" />
                <test value="1.0">
                   propulsion/engine/set-running GT 0
                </test>
            </switch>

            <fcs_function name="aero/function/engine-exhaust-thrust">
                <function>
                    <product>
                        <property>aero/function/running-factor</property>
                        <property>propulsion/engine/propeller-rpm</property>
                        <value>0.00079365079</value> <!-- 1/1260 to nomalize engine/rpm -->
                        <property> propulsion/engine/map-inhg </property>
                        <value>0.01234567</value> <!-- 1/81 inhg to nomalize engine/map-inhg -->
                        <value> 200 </value> <!-- 200 lbs of thrust at full RPM and map -->
                    </product>
                </function>
                <output> external_reactions/exhaust-thrust/magnitude </output>
            </fcs_function>

        </channel>

        <channel name="Pitch">		

            <aerosurface_scale name="Elevator Control">
                <input>fcs/pitch-trim-cmd-norm</input>
                <range>
                    <min>-0.4455</min>
                    <max>0.4455</max>
                </range>
                <output>fcs/pitch-trim-cmd-norm-scaled</output>
            </aerosurface_scale>

            <summer name="Pitch Trim Offest Bias">
                <input>fcs/pitch-trim-cmd-norm-scaled</input>
                <bias>0.02546</bias>
                <clipto>
                    <min>-1.0</min>
                    <max>1.0</max>
                </clipto>
                <output>fcs/pitch-trim-cmd-norm-offset-biased</output>
            </summer>
            
            <summer name="Pitch Trim Sum Not Scaled">
                <input>fcs/elevator-cmd-norm</input>
                <input>fcs/pitch-trim-cmd-norm-offset-biased</input>
                <clipto>
                    <min>-1.7</min>
                    <max>1.7</max>
                </clipto>
            </summer>

            <pure_gain name="Pitch Trim Sum">
                <input>fcs/pitch-trim-sum-not-scaled</input>
                <gain> 0.5 </gain>
                <output>fcs/pitch-trim-sum</output>
            </pure_gain>

            <aerosurface_scale name="Elevator Control">
                <input>fcs/pitch-trim-sum</input>
                <range>
                    <min>-1.0</min>
                    <max>1.0</max>
                </range>
                <output>fcs/elevator-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Elevator Position Normalized">
                <input>fcs/elevator-pos-rad</input>
                <domain>
                    <min>-0.78</min>
                    <max>0.78</max>
                </domain>
                <range>
                   <min>-1.0</min>
                   <max>1.0</max>
                </range>
                <output>fcs/elevator-pos-norm</output>
            </aerosurface_scale>
            
          <fcs_function name="Elevator Position Animation">
            <function>
              <sum>
                 <product>
                   <value> 0.8 </value>
                   <property>fcs/elevator-pos-norm</property>
                   <value>57.2957795</value>
                 </product>
                 <product>
                   <value> -13 </value>
                   <property>/controls/flight/elevator-trim</property>
                 </product>
                </sum>
                </function>
                <output>/surface-positions/elevator-pos-norm</output>
            </fcs_function>
			
	<fcs_function name="aero/pitch-moment-damping-factor">
	<function>
	  <description>pitch damping during take off</description>
	  <product>
	  <property>gear/wow</property>
	  <value>0.2</value>
	  <table>
        <independentVar lookup="row">aero/alpha-deg</independentVar>
		<independentVar lookup="column">velocities/vc-kts</independentVar>
		<independentVar lookup="table">aero/alphadot-deg_sec</independentVar> 
           <tableData breakPoint="-10.0">
		   		     70          80 
           -4.25    5.0         1.0  
           -3.25    10.0        1.0 
           -2.25    25.0        1.0 
           -1.25    25.0        1.0 
           -0.25    15.0        1.0 
            0.75    10.0        1.0  
            1.75    1.0         1.0  
    		2.75 	1.0         1.0
	    	3.75 	1.0         1.0
		    4.75    1.0         1.0	
     		5.75 	1.0         1.0
            6.75    1.0         1.0
			7.75    1.0         1.0
			</tableData>			
			<tableData breakPoint="0.0">
		             70          80 
           -4.25    1.0         1.0  
           -3.25    1.0         1.0 
           -2.25    1.0         1.0 
           -1.25    1.0         1.0 
           -0.25    1.0         1.0 
            0.75    1.0         1.0  
            1.75    1.0         1.0  
    		2.75 	1.0         1.0
	    	3.75 	1.0         1.0
		    4.75    1.0         1.0	
     		5.75 	1.0         1.0
            6.75    1.0         1.0
			7.75    1.0         1.0
			</tableData>
		    <tableData breakPoint="10.0">
                   70          80 
           -4.25    1.0         1.0  
           -3.25    1.0         1.0 
           -2.25    1.0         1.0 
           -1.25    1.0         1.0 
           -0.25    1.0         1.0 
            0.75    1.0         1.0  
            1.75    1.0         1.0  
    		2.75 	10.0        1.0
	    	3.75 	15.0        1.0
		    4.75    25.0        1.0	
     		5.75 	25.0        1.0
            6.75    10.0        1.0
			7.75    5.0         1.0
			</tableData>
      </table>
	  </product>
	  </function>
	  <clipto>
          <min>1.0</min>
		  <max>100</max>
       </clipto>
	  <output>aero/pitch-moment-damping-factor</output>
	</fcs_function>
            
        </channel>
        
        <channel name="guns">
        
           <switch name="systems/armament/innerGunsFiring">
             <default value="0" />
             <test logic="AND" value="1">
                /controls/armament/gun-trigger > 0
                /ai/submodels/submodel[6]/count > 0
             </test>
           </switch> 

           <switch name="systems/armament/outerGunsFiring">
             <default value="0" />
             <test logic="AND" value="1">
                /controls/armament/gun-trigger > 0
                /ai/submodels/submodel[8]/count > 0
             </test>
           </switch>    

           <switch name="systems/armament/ejectionAnimatedOuter">
             <default value="0" />
             <test logic="AND" value="1">
                /sim/frame-rate > 30
                systems/armament/outerGunsFiring > 0
                /sim/current-view/internal == 0
             </test>
           </switch>   
           
           <switch name="systems/armament/ejectionAnimatedInner">
             <default value="0" />
             <test logic="AND" value="1">
                /sim/frame-rate > 30
                systems/armament/innerGunsFiring > 0
                /sim/current-view/internal == 0
             </test>
           </switch> 

           <switch name="systems/armament/gunSmokeAnimatedInner">
             <default value="0" />
             <test logic="AND" value="1">
                /sim/frame-rate > 27
                systems/armament/innerGunsFiring > 0
             </test>
           </switch>   

           <switch name="systems/armament/gunSmokeAnimatedOuter">
             <default value="0" />
             <test logic="AND" value="1">
                /sim/frame-rate > 27
                systems/armament/outerGunsFiring > 0
             </test>
           </switch>           

           <switch name="systems/armament/muzzleFlashAnimatedOuter">
             <default value="0" />
             <test logic="AND" value="1">
                /sim/frame-rate > 25
                systems/armament/outerGunsFiring > 0
             </test>
           </switch>
           
           <switch name="systems/armament/muzzleFlashAnimatedInner">
             <default value="0" />
             <test logic="AND" value="1">
                /sim/frame-rate > 25
                systems/armament/innerGunsFiring > 0
             </test>
           </switch>
           
        </channel>
        
        <channel name="Roll">
            <pure_gain name="Roll Trim Scaled">
                <input>fcs/roll-trim-cmd-norm</input>
                <gain> 0.5 </gain>
                <output>fcs/roll-trim-scaled</output>
            </pure_gain>
            
            <summer name="Roll Trim Sum">
                <input>fcs/aileron-cmd-norm</input>
                <input>fcs/roll-trim-scaled</input>
                <clipto>
                    <min>-1.3</min>
                    <max>1.3</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Left Aileron Control">
                <input>fcs/roll-trim-sum</input>
                <range>
                    <min>-0.35</min>
                    <max>0.35</max>
                </range>
                <output>fcs/left-aileron-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right Aileron Control">
                <input>-fcs/roll-trim-sum</input>
                <range>
                    <min>-0.35</min>
                    <max>0.35</max>
                </range>
                <output>fcs/right-aileron-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Left Aileron Position Normalized">
                <input>fcs/left-aileron-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max>0.35</max>
                </domain>
                <range>
                   <min>-1.0</min>
                   <max>1.0</max>
                </range>
                <output>fcs/left-aileron-pos-norm</output>
            </aerosurface_scale>

            <aerosurface_scale name="Right Aileron Position Normalized">
                <input>fcs/right-aileron-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max>0.35</max>
                </domain>
                <range>
                   <min>-1.0</min>
                   <max>1.0</max>
                </range>
                <output>fcs/right-aileron-pos-norm</output>
            </aerosurface_scale>
            
          <fcs_function name="Aileron Position Animation Right">
            <function>
              <sum>
                 <product>
                   <value> 0.8 </value>
                   <value>57.2957795</value>
                   <property>fcs/right-aileron-pos-norm</property>
                 </product>
                 <product>
                   <value> 22 </value>
                   <property>/controls/flight/aileron-trim</property>
                 </product>
                </sum>
                </function>
                <output>/surface-positions/right-aileron-pos-norm</output>
            </fcs_function>
            
         <fcs_function name="Aileron Position Animation Left">
            <function>
              <sum>
                 <product>
                   <value> -0.8 </value>
                   <value>57.2957795</value>
                   <property>fcs/right-aileron-pos-norm</property>
                 </product>
                 <product>
                   <value> -22 </value>
                   <property>/controls/flight/aileron-trim</property>
                 </product>
                </sum>
                </function>
                <output>/surface-positions/left-aileron-pos-norm</output>
            </fcs_function>

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

            <aerosurface_scale name="yaw trim scaled">
                <input>fcs/yaw-trim-cmd-norm</input>
                <range>
                    <min>-0.5</min>
                    <max>0.5</max>
                </range>
                <output>fcs/yaw-trim-scaled</output>
            </aerosurface_scale>
            
            <summer name="Rudder Command Sum">
                <input>fcs/rudder-cmd-norm</input>
                <input>fcs/yaw-trim-scaled</input>
                <clipto>
                    <min>-1</min>
                    <max>1</max>
                </clipto>
            </summer>

            <aerosurface_scale name="Rudder Control">
                <input>fcs/rudder-command-sum</input>
                <range>
                    <min>-0.35</min>
                    <max>0.35</max>
                </range>
                <output>fcs/rudder-pos-rad</output>
            </aerosurface_scale>

            <aerosurface_scale name="Rudder Position Normalized">
                <input>fcs/rudder-pos-rad</input>
                <domain>
                    <min>-0.35</min>
                    <max>0.35</max>
                </domain>
                <range>
                   <min>-1.0</min>
                   <max>1.0</max>
                </range>
                <output>fcs/rudder-pos-norm</output>
            </aerosurface_scale>
            
          <fcs_function name="rudder Position Animation">
            <function>
              <sum>
                 <product>
                   <value> 1 </value>
                   <property>fcs/rudder-pos-deg</property>
                 </product>
                 <product>
                   <value> 10 </value>
                   <property>/controls/flight/rudder-trim</property>
                 </product>
                </sum>
                </function>
                <output>/surface-positions/rudder-pos-norm</output>
            </fcs_function>

        </channel>

        <channel name="Flaps">
            <kinematic name="Flaps Control">
                <input>fcs/flap-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>10</position>
                        <time>3</time>
                    </setting>
                    <setting>
                        <position>20</position>
                        <time>3</time>
                    </setting>
                    <setting>
                        <position>30</position>
                        <time>3</time>
                    </setting>
                    <setting>
                        <position>40</position>
                        <time>3</time>
                    </setting>
                    <setting>
                        <position>47</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>  <!-- Flaps actual minimum position -->
                <max>47</max>  <!-- Flaps actual maximum position -->
              </domain>
              <range>
                <min>0</min>  <!-- Flaps normalized minimum position -->
                <max>1</max>  <!-- Flaps normalized maximum position -->
              </range>
              <output>fcs/flap-pos-norm</output>
            </aerosurface_scale>
        </channel>
        
        <channel name="Landing Gear">
            <kinematic name="Gear Control up">
                <input>gear/gear-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>14.1</time>
                    </setting>
                </traverse>
                <output>gear/gear-pos-norm-up</output>
            </kinematic>
            
            <kinematic name="Gear Control down">
                <input>gear/gear-cmd-norm</input>
                <traverse>
                    <setting>
                        <position>0</position>
                        <time>0</time>
                    </setting>
                    <setting>
                        <position>1</position>
                        <time>8.1</time>
                    </setting>
                </traverse>
                <output>gear/gear-pos-norm-down</output>
            </kinematic>
            
           <switch name="gearPosTimed">
              <default value="0.0"/>
              <test value="gear/gear-pos-norm-up">
                 gear/gear-cmd-norm == 0
              </test>
              <test value="gear/gear-pos-norm-down">
                 gear/gear-cmd-norm == 1
              </test>
              <output>gear/gear-pos-norm</output>
            </switch>
           
        </channel>

        <channel name="Brakes">

           <summer name="systems/brakes/brake-left">
                <input>/controls/gear/brake-left</input>
                <input>/controls/gear/brake-parking</input>
                <clipto>
                    <min>0</min>
                    <max>0.69</max>
                </clipto>
            </summer>

            <summer name="systems/brakes/brake-right">
                <input>/controls/gear/brake-right</input>
                <input>/controls/gear/brake-parking</input>
                <clipto>
                    <min>0</min>
                    <max>0.69</max>
                </clipto>
            </summer>            
                        
            <fcs_function name="systems/brakes/brake-scaling">
                <function>
                    <table> 
                        <independentVar lookup="row">velocities/vg-fps</independentVar>
						<independentVar lookup="column">gear/unit[2]/compression-ft</independentVar>
						<independentVar lookup="table">propulsion/engine/map-inhg</independentVar>
                        <tableData breakPoint="11.0">
						        0.05   0.25    
                            0   0.15    1.2    
							15  0.075   1.0    
                            24  0.3     1.0   
							50  0.6     1.0
                        </tableData>
						<tableData breakPoint="20.0">
						        0.05    0.25    
                            0   0.4     1.8    
							15  0.3     1.5    
                            24  0.3     1.0   
							50  0.6     1.0
                        </tableData>
						<tableData breakPoint="30.0">
						        0.05    0.25    
                            0   0.5     2.5    
							15  0.4     2.0    
                            24  0.3     1.0   
							50  0.6     1.0
                        </tableData>
                    </table>
                </function>
            </fcs_function>
            
            <fcs_function name="Brake left">
               <function>
                   <product>
                      <property>systems/brakes/brake-left</property>
                      <property>systems/brakes//brake-scaling</property>
                   </product>
               </function>
               <output>fcs/left-brake-cmd-norm</output>
            </fcs_function>
            
            <fcs_function name="Brake right">
               <function>
                   <product>
                      <property>systems/brakes/brake-right</property>
                      <property>systems/brakes//brake-scaling</property>
                   </product>
               </function>
               <output>fcs/right-brake-cmd-norm</output>
            </fcs_function>

        </channel>
        
        <channel name="clipping">
        
           <pure_gain name="fcs/qbar-psf_clipped">
	         <description>qbar-psf_clipped</description>
	         <input>aero/qbar-psf</input> 
             <gain>1.0</gain>             
             <clipto>
                <min>-1000.0</min>
                <max>10000.0</max>
             </clipto>         
	      </pure_gain>
        
        </channel>

    </flight_control>

    <external_reactions>
    
        <force name="exhaust-thrust" frame="BODY">
            <location unit="IN">
            <x>  36  </x> <!-- center of engine -->
            <y>    0.0 </y>
            <z>    0.0 </z>
            </location>
            <direction>
            <x>    1.0 </x> <!-- straight down the aircraft longitudinal axis -->
            <y>    0.0 </y>
            <z>    0.0 </z>
            </direction>
        </force>
    
    </external_reactions>


    <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>
        
    <function name="aero/thrust-qbar_psf">
        <description>Dynamic_pressure_including_backwash</description>
        <sum>
            <product>
                <v> 0.5 </v>
                <p>atmosphere/rho-slugs_ft3</p>
                <pow>
                    <product>
                        <p> propulsion/engine/prop-induced-velocity_fps </p>
                        <v> 2.0 </v>
                    </product>
                    <v> 2.0 </v>
                </pow>        
            </product>
            <p>aero/qbar-psf</p>
        </sum>      
    </function>

        <axis name="DRAG">

            <!--
               Add in parisitic drag for fuselage etc.  Since
               "aero/coefficient/CDalpha" is the wing alone.
            -->
           <function name="aero/coefficient/CDo">
                <description>Drag_due_to_non_wing_components</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <value> 0.62 </value>
                    <table>
                      <independentVar lookup="row">aero/alpha-deg</independentVar>
                      <tableData>  
                          -90        0.25
                          -30        0.07
                          -15        0.03518
                          -12.5      0.02613
                          -10        0.02010
                          -7.5       0.01608
                          -5         0.01357
                          -2.5       0.01226
                          0          0.01216
                          2.5        0.01226
                          5          0.01357
                          7.5        0.01608
                          10         0.02010
                          12.5       0.02613
                          15         0.03518
                          30         0.07
                          90         0.25
                      </tableData>
                  </table>
                </product>
            </function>

            <!--
                 Cooling drag including Merideth Effect
                 Shuold be about 20% of total drag below mach 0.22
                 Should be about 3% of total drag above mach 0.6
            -->

            <function name="aero/coefficient/CDcooling">
                <description>Drag_due_to_cooling</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <value> 0.0165 </value>
                    <pow>
                        <table>
                            <independentVar lookup="row">velocities/vc-kts</independentVar>
                            <tableData>
                                    0        1.0
                                    135      0.99
                                    174      0.37
                                    440      0.001
                            </tableData>
                        </table>
                        <value> 2.0 </value>
                    </pow>
                </product>
            </function>


            <function name="aero/coefficient/CDalpha">
                <description>Drag_due_to_alpha</description>
                    <!--
                      Drag as calculated by XFOIL for a blended section.
                      BL 17.5 was used for the root section and BL 215
                      for the tip section.  XFOIL was only able to generate
                      polars for +- 42 degrees alpha.  Other values were
                      generated wth JavaFoil and blended into the XFOIL polars.

                      This is the wing only
                    -->
                    <product>
                        <property>aero/qbar-psf</property>
                        <property>metrics/Sw-sqft</property>
                        <!--
                            increase drag to reflect real world conditions since 
                            otherwise this would be an idealized prefect wing only.
                        -->
                         <value> 2.5 </value>
                        <table>
                        <independentVar>aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/Re</independentVar>
                          <tableData>
                                     2500000    5000000    7000000     10000000   20000000    30000000    40000000
                            -180.00  0.01196    0.01196    0.01196     0.01196    0.01196     0.01196     0.01196
                            -150.00  0.1045     0.1045     0.1045      0.1045     0.1045      0.1045      0.1045
                            -120.00  0.516      0.516      0.516       0.516      0.516       0.516       0.516
                            -90.000  0.505      0.505      0.505       0.505      0.505       0.505       0.505
                            -60.000  1.0429     1.0429     1.0429      1.0429     1.0429      1.0429      1.0429
                            -42.000  0.43463    0.43463    0.43408     0.43408    0.43408     0.43407     0.43407
                            -41.000  0.43158    0.43158    0.43456     0.43408    0.43408     0.43407     0.43407
                            -40.000  0.42793    0.42793    0.43109     0.43142    0.43142     0.43141     0.43141
                            -39.000  0.42372    0.42372    0.42727     0.42840    0.42840     0.42839     0.42839
                            -38.000  0.41876    0.41876    0.42301     0.42469    0.42469     0.42466     0.42466
                            -37.000  0.41265    0.41374    0.41745     0.41935    0.41935     0.4193      0.4193
                            -36.000  0.40449    0.40768    0.40923     0.41174    0.41174     0.41173     0.41173
                            -35.000  0.39577    0.40054    0.40084     0.40271    0.40271     0.40272     0.40272
                            -34.000  0.38701    0.39258    0.39244     0.39434    0.39434     0.39433     0.39433
                            -33.000  0.37362    0.38395    0.38227     0.38552    0.38552     0.38551     0.38551
                            -32.000  0.36801    0.37466    0.37388     0.37622    0.37622     0.37621     0.37621
                            -31.000  0.35901    0.36473    0.36495     0.36642    0.36642     0.36641     0.36641
                            -30.000  0.34928    0.35433    0.35546     0.35321    0.35321     0.35622     0.35622
                            -29.500  0.34419    0.34891    0.35049     0.34848    0.34848     0.34849     0.34849
                            -29.000  0.34334    0.34334    0.34536     0.34375    0.34375     0.31719     0.31835
                            -28.500  0.33766    0.33766    0.34004     0.33890    0.31344     0.30762     0.31343
                            -28.000  0.33183    0.33183    0.33429     0.33183    0.30848     0.30235     0.30171
                            -27.500  0.32358    0.32358    0.32358     0.32358    0.30343     0.29711     0.29165
                            -27.000  0.31869    0.31869    0.31869     0.31869    0.29827     0.28743     0.28606
                            -26.500  0.30802    0.31358    0.31358     0.31358    0.28924     0.28161     0.28044
                            -26.000  0.30310    0.30820    0.31122     0.31122    0.28352     0.27587     0.27007
                            -25.500  0.29794    0.30254    0.30110     0.30519    0.27402     0.26592     0.25985
                            -25.000  0.29256    0.29660    0.29565     0.29906    0.26754     0.25968     0.12136
                            -24.500  0.28697    0.25687    0.29009     0.25687    0.25725     0.1800      0.08937
                            -24.000  0.28118    0.24840    0.28437     0.24840    0.21841     0.08923     0.07347
                            -23.500  0.27517    0.23805    0.26406     0.23805    0.12000     0.07317     0.06277
                            -23.000  0.25747    0.22747    0.23477     0.22747    0.08450     0.06234     0.05422
                            -22.500  0.23282    0.22282    0.22065     0.21586    0.06918     0.05381     0.04752
                            -22.000  0.21173    0.21173    0.15962     0.09060    0.05887     0.04711     0.04184
                            -21.500  0.20044    0.20044    0.08962     0.07237    0.05083     0.04149     0.03702
                            -21.000  0.18635    0.18635    0.07082     0.06035    0.04450     0.03672     0.03292
                            -20.500  0.18553    0.09917    0.05909     0.05151    0.03923     0.03280     0.02916
                            -20.000  0.16798    0.06906    0.05063     0.04470    0.03479     0.02928     0.02609
                            -19.500  0.13430    0.05705    0.04408     0.03915    0.03111     0.02607     0.02371
                            -19.000  0.10491    0.04870    0.03878     0.03456    0.02792     0.02342     0.02118
                            -18.500  0.06569    0.04241    0.03440     0.03067    0.02497     0.02116     0.01955
                            -18.000  0.05381    0.03738    0.03069     0.02736    0.02262     0.01944     0.01799
                            -17.500  0.04584    0.03323    0.02754     0.02451    0.02025     0.01794     0.01664
                            -17.000  0.03998    0.02976    0.02487     0.02208    0.01870     0.01661     0.01548
                            -16.500  0.03544    0.02682    0.02260     0.01985    0.01732     0.01548     0.01453
                            -16.000  0.02957    0.02312    0.02072     0.01815    0.01611     0.01457     0.01383
                            -15.500  0.02593    0.02080    0.01881     0.01694    0.01513     0.01387     0.01313
                            -15.000  0.02343    0.01852    0.01749     0.01590    0.01389     0.01316     0.01247
                            -14.500  0.02144    0.01731    0.01604     0.01509    0.01305     0.01236     0.01186
                            -14.000  0.01982    0.01631    0.01509     0.01432    0.01239     0.01159     0.01120
                            -13.500  0.01793    0.01552    0.01446     0.01341    0.01179     0.01098     0.01056
                            -13.000  0.01677    0.01443    0.01350     0.01259    0.01124     0.01046     0.01000
                            -12.500  0.01598    0.01352    0.01283     0.01191    0.01065     0.00998     0.00953
                            -12.000  0.01492    0.01269    0.01193     0.01132    0.01015     0.00954     0.00911
                            -11.500  0.01410    0.01193    0.01120     0.01059    0.00956     0.00908     0.00871
                            -11.000  0.01354    0.01134    0.01056     0.00995    0.00909     0.00859     0.00831
                            -10.500  0.01271    0.01074    0.01010     0.00942    0.00857     0.00818     0.00788
                            -10.000  0.01222    0.01031    0.00958     0.00903    0.00811     0.00773     0.00751
                            -9.500   0.01146    0.00977    0.00919     0.00858    0.00770     0.00732     0.00712
                            -9.000   0.01102    0.00936    0.00887     0.00825    0.00741     0.00697     0.00675
                            -8.500   0.01039    0.00890    0.00838     0.00788    0.00708     0.00672     0.00645
                            -8.000   0.00991    0.00853    0.00800     0.00756    0.00682     0.00643     0.00622
                            -7.500   0.00948    0.00815    0.00765     0.00723    0.00654     0.00621     0.00597
                            -7.000   0.00914    0.00782    0.00732     0.00692    0.00628     0.00596     0.00576
                            -6.500   0.00882    0.00755    0.00713     0.00669    0.00602     0.00573     0.00556
                            -6.000   0.00842    0.00726    0.00684     0.00643    0.00580     0.00550     0.00531
                            -5.500   0.00810    0.00704    0.00662     0.00624    0.00562     0.00534     0.00515
                            -5.000   0.00781    0.00680    0.00640     0.00605    0.00546     0.00517     0.00502
                            -4.500   0.00749    0.00657    0.00623     0.00587    0.00531     0.00505     0.00489
                            -4.000   0.00695    0.00632    0.00600     0.00568    0.00517     0.00494     0.00478
                            -3.500   0.00632    0.00590    0.00570     0.00548    0.00505     0.00481     0.00467
                            -3.000   0.00531    0.00547    0.00531     0.00516    0.00486     0.00470     0.00457
                            -2.500   0.00438    0.00477    0.00494     0.00486    0.00465     0.00453     0.00446
                            -2.000   0.00430    0.00414    0.00433     0.00451    0.00445     0.00438     0.00438
                            -1.500   0.00427    0.00367    0.00379     0.00405    0.00426     0.00424     0.00430
                            -1.000   0.00431    0.00365    0.00348     0.00365    0.00404     0.00416     0.00428
                            -0.500   0.00435    0.00361    0.00342     0.00332    0.00381     0.00407     0.00429
                            0.000    0.00439    0.00366    0.00342     0.00325    0.00361     0.00399     0.00430
                            0.500    0.00449    0.00369    0.00346     0.00329    0.00325     0.00382     0.00424
                            1.000    0.00446    0.00375    0.00354     0.00335    0.00335     0.00370     0.00422
                            1.500    0.00453    0.00381    0.00359     0.00344    0.00361     0.00409     0.00425
                            2.000    0.00463    0.00388    0.00372     0.00364    0.00423     0.00433     0.00444
                            2.500    0.00468    0.00405    0.00394     0.00409    0.00456     0.00459     0.00456
                            3.000    0.00477    0.00432    0.00446     0.00491    0.00490     0.00477     0.00472
                            3.500    0.00496    0.00491    0.00535     0.00534    0.00521     0.00501     0.00490
                            4.000    0.00529    0.00594    0.00595     0.00585    0.00544     0.00525     0.00512
                            4.500    0.00652    0.00664    0.00644     0.00613    0.00571     0.00555     0.00544
                            5.000    0.00751    0.00704    0.00676     0.00648    0.00614     0.00590     0.00569
                            5.500    0.00819    0.00748    0.00720     0.00704    0.00646     0.00612     0.00590
                            6.000    0.00875    0.00812    0.00781     0.00745    0.00673     0.00636     0.00614
                            6.500    0.00953    0.00864    0.00820     0.00775    0.00701     0.00664     0.00641
                            7.000    0.01021    0.00907    0.00856     0.00808    0.00731     0.00692     0.00666
                            7.500    0.01074    0.00947    0.00895     0.00847    0.00764     0.00721     0.00694
                            8.000    0.01127    0.00990    0.00936     0.00886    0.00796     0.00751     0.00722
                            8.500    0.01180    0.01036    0.00989     0.00924    0.00831     0.00785     0.00769
                            9.000    0.01235    0.01084    0.01022     0.00962    0.00869     0.00842     0.00810
                            9.500    0.01295    0.01131    0.01066     0.01012    0.00934     0.00884     0.00846
                            10.000   0.01345    0.01181    0.01117     0.01075    0.00983     0.00925     0.00893
                            10.500   0.01416    0.01235    0.01205     0.01158    0.01041     0.01041     0.00933
                            11.000   0.01470    0.01209    0.01279     0.01209    0.01094     0.01094     0.00975
                            11.500   0.01564    0.01424    0.01361     0.01266    0.01150     0.01074     0.01020
                            12.000   0.01726    0.01513    0.01437     0.01337    0.01205     0.01126     0.01068
                            12.500   0.01881    0.01641    0.01519     0.01415    0.01272     0.01178     0.01118
                            13.000   0.02060    0.01786    0.01621     0.01503    0.01352     0.01239     0.01167
                            13.500   0.02271    0.01961    0.01750     0.01613    0.01480     0.01311     0.01228
                            14.000   0.02484    0.02134    0.01898     0.01740    0.01545     0.01393     0.01301
                            14.500   0.02713    0.02326    0.02062     0.01885    0.01661     0.01483     0.01380
                            15.000   0.02978    0.02541    0.02247     0.02046    0.01824     0.01581     0.01469
                            15.500   0.03280    0.02786    0.02454     0.02229    0.01986     0.01691     0.01568
                            16.000   0.03633    0.03063    0.02685     0.02437    0.02221     0.01824     0.01677
                            16.500   0.04039    0.03376    0.02950     0.02668    0.02469     0.01962     0.01798
                            17.000   0.04521    0.03741    0.03249     0.02932    0.02751     0.02144     0.01929
                            17.500   0.05082    0.04156    0.03587     0.03234    0.03070     0.02353     0.02097
                            18.000   0.05745    0.04639    0.03981     0.03573    0.03285     0.02580     0.02290
                            18.500   0.06534    0.05203    0.04422     0.03972    0.03598     0.02821     0.02514
                            19.000   0.07493    0.05855    0.04939     0.04413    0.03976     0.03095     0.02768
                            19.500   0.08683    0.06620    0.05535     0.04938    0.04393     0.03413     0.03052
                            20.000   0.10232    0.07506    0.06215     0.05535    0.04881     0.03754     0.03370
                            20.500   0.12315    0.08580    0.07017     0.06213    0.05422     0.04150     0.03709
                            21.000   0.14902    0.10031    0.07940     0.07017    0.06069     0.04598     0.04083
                            21.500   0.17301    0.12225    0.09028     0.07954    0.06811     0.05078     0.04538
                            22.000   0.20180    0.16099    0.10366     0.09057    0.07671     0.05665     0.05011
                            22.500   0.22724    0.19728    0.12353     0.10274    0.08691     0.06297     0.05579
                            23.000   0.24078    0.21848    0.15543     0.11848    0.10019     0.07013     0.06176
                            23.500   0.25157    0.23034    0.20014     0.14270    0.11726     0.07854     0.06903
                            24.000   0.26130    0.24268    0.22756     0.17738    0.15000     0.08853     0.07714
                            24.500   0.27017    0.25475    0.24323     0.22145    0.22145     0.09994     0.08638
                            25.000   0.27904    0.27268    0.25524     0.24608    0.24079     0.11421     0.09674
                            25.500   0.28834    0.28475    0.26725     0.25834    0.25597     0.12821     0.10963
                            26.000   0.30448    0.29496    0.29691     0.26897    0.26762     0.15393     0.12565
                            26.500   0.31412    0.30134    0.30293     0.27918    0.27557     0.20013     0.14276
                            27.000   0.32068    0.31068    0.32541     0.28990    0.28000     0.25845     0.16845
                            27.500   0.32682    0.32682    0.33141     0.30460    0.29500     0.28480     0.20526
                            28.000   0.33274    0.33274    0.33685     0.30498    0.30500     0.29190     0.27190
                            28.500   0.33851    0.33851    0.34685     0.31107    0.32000     0.31325     0.29600
                            29.000   0.34435    0.34435    0.35435     0.31785    0.32861     0.31944     0.30944
                            29.500   0.35083    0.35083    0.36163     0.32363    0.33363     0.32363     0.31971
                            30.000   0.35639    0.35639    0.36788     0.33891    0.33908     0.32535     0.32535
                            31.000   0.36674    0.36674    0.37969     0.34892    0.35192     0.34245     0.34047
                            32.000   0.37639    0.37639    0.39020     0.35831    0.36100     0.35598     0.35062
                            33.000   0.38552    0.38552    0.39981     0.36428    0.36428     0.36522     0.36428
                            34.000   0.39419    0.39419    0.40870     0.37317    0.37317     0.37317     0.37317
                            35.000   0.40240    0.40240    0.41699     0.38128    0.38128     0.38128     0.38128
                            36.000   0.40939    0.40939    0.42360     0.38811    0.38811     0.38811     0.38811
                            37.000   0.41535    0.41535    0.43120     0.394      0.394       0.394       0.394
                            38.000   0.42122    0.42122    0.39982     0.39982    0.39982     0.39982     0.39982
                            39.000   0.42628    0.42628    0.40716     0.40716    0.40481     0.40481     0.40481
                            40.000   0.43095    0.43095    0.40944     0.40944    0.40944     0.40944     0.40944
                            41.000   0.43535    0.43535    0.41381     0.41381    0.41381     0.41381     0.41381
                            42.000   0.43952    0.43952    0.41796     0.41796    0.41796     0.41796     0.41796
                            60.000   1.085      1.085      1.085       1.085      1.085       1.085       1.085
                            90.000   1.3564     1.3564     1.3564      1.3564     1.3564      1.3564      1.3564
                            120.00   0.479      0.479      0.479       0.479      0.479       0.479       0.479
                            150.00   0.104      0.104      0.104       0.104      0.104       0.104       0.104
                            180.00   0.0119     0.0119     0.0119      0.0119     0.0119      0.0119      0.0119
                          </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>0.0125</value> <!-- based on NACA X51 data -->
                </product>
            </function>

            <!-- from NACA P-51X and P-51B test data -->
            <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>
                            0.00    0.00000
                            0.62    0.00000
                            0.64    0.00100
                            0.66    0.00200
                            0.68    0.00500
                            0.70    0.01250
                            0.72    0.02000
                            0.74    0.03000
                            0.76    0.04300
                            0.78    0.06000
                            0.80    0.08000
                            0.82    0.10000
                            0.84    0.12500  <!-- guesses to extend the table -->
                            0.86    0.15500  
                            0.88    0.20000
                            0.90    0.26000
                            0.92    0.35000
                            1.00    0.60000
                        </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>aero/beta-rad</independentVar>
                          <tableData>
                              -1.5700        0.500
                              -0.2600        0.0100
                              0.0000         0.0000
                              0.2600         0.0100
                              1.5700         0.500
                          </tableData>
                      </table>
                </product>
            </function>

            <!-- The rest of the drag functions are guesses.
                 These attempt to get flight characteristics
                 that approximate information is various sources
                 such as pilots reports and various NACA documents
                 that have information about how the P-51 is
                 affected by these drag sources.
                 -->

            <function name="aero/coefficient/CDflaps">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <value>0.04</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>0.023</value>
                </product>
            </function>

            <function name="aero/coefficient/CDde">
                <description>Drag_due_to_Elevator_Deflection</description>
                    <product>
                        <property>aero/qbar-psf</property>
                        <property>metrics/Sh-sqft</property>
                        <table>
                            <independentVar>fcs/elevator-pos-norm</independentVar>
                            <tableData>
                               -1.0    1.0
                                0.0    0.0
                                1.0    1.0
                            </tableData>
                        </table>
                        <value>0.05</value>
                    </product>
            </function>

            <function name="aero/coefficient/CDda">
                <description>Drag_due_to_Aileron_Deflection</description>
                    <product>
                        <property>aero/qbar-psf</property>
                        <property>metrics/Sw-sqft</property>
                        <value> 0.8 </value>
                        <table>
                            <independentVar>fcs/left-aileron-pos-norm</independentVar>
                            <tableData>
                               -1.0    1.034
                                0.0    0.034
                                0.034    0.0
                                1.0    0.966
                            </tableData>
                        </table>
                        <value>0.006</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">

           <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>
                    <value> 0.92 </value>
                    <table>
                         <!--
                                Drag as calculated by XFOIL for a blended section.
                                BL 17.5 was used for the root section and BL 215
                                for the tip section.  XFOIL was only able to generate
                                polars for +- 42 degrees alpha.  Other values were
                                generated wth JavaFoil and blended into the XFOIL polars.
                          -->
                          <independentVar lookup="row">aero/alpha-deg</independentVar>
                          <independentVar lookup="column">aero/Re</independentVar>
                          <tableData>
                                     2500000   5000000  7000000   10000000   20000000 30000000   40000000
                            -180.00  -0.168    -0.168   -0.168    -0.168    -0.168    -0.168     -0.168
                            -150.00  -0.270    -0.270   -0.270    -0.270    -0.270    -0.270     -0.270
                            -120.00  -0.048    -0.048   -0.048    -0.048    -0.048    -0.048     -0.048
                            -90.000  -0.032    -0.032   -0.032    -0.032    -0.032    -0.032     -0.032
                            -60.000  -0.6      -0.6     -0.6      -0.6      -0.6      -0.6       -0.6
                            -42.000  -1.2098   -1.2098  -1.2098   -1.2132   -1.2132   -1.2132    -1.2132
                            -41.000  -1.2003   -1.2003  -1.2124   -1.2132   -1.2132   -1.2132    -1.2132
                            -40.000  -1.1883   -1.1883  -1.2004   -1.2026   -1.2026   -1.2025    -1.2025
                            -39.000  -1.1739   -1.1739  -1.1864   -1.1898   -1.1898   -1.1898    -1.1898
                            -38.000  -1.1569   -1.1569  -1.1707   -1.1748   -1.1748   -1.1748    -1.1748
                            -37.000  -1.1378   -1.1474  -1.1534   -1.1577   -1.1577   -1.1577    -1.1577
                            -36.000  -1.1165   -1.1303  -1.1340   -1.1392   -1.1392   -1.1392    -1.1392
                            -35.000  -1.0945   -1.1111  -1.1138   -1.1184   -1.1184   -1.1185    -1.1185
                            -34.000  -1.0713   -1.0899  -1.0926   -1.0974   -1.0974   -1.0974    -1.0974
                            -33.000  -1.0421   -1.0668  -1.0700   -1.0749   -1.0749   -1.0749    -1.0749
                            -32.000  -1.0209   -1.0419  -1.0465   -1.0509   -1.0509   -1.0509    -1.0509
                            -31.000  -0.9937   -1.0150  -1.0213   -1.0255   -1.0255   -1.0255    -1.0255
                            -30.000  -0.9644   -0.9869  -0.9946   -0.9986   -0.9986   -0.9989    -0.9989
                            -29.500  -0.9494   -0.9723  -0.9807   -0.9852   -0.9852   -0.9852    -0.9852
                            -29.000  -0.9574   -0.9574  -0.9664   -0.9714   -0.9714   -1.0003    -0.9942
                            -28.500  -0.9423   -0.9423  -0.9517   -0.9572   -0.9807   -0.9939    -0.9807
                            -28.000  -0.9268   -0.9268  -0.9362   -0.9268   -0.9671   -0.9810    -0.9806
                            -27.500  -0.9115   -0.9115  -0.9115   -0.9115   -0.9533   -0.9677    -0.9804
                            -27.000  -0.8961   -0.8961  -0.8961   -0.8961   -0.9392   -0.9619    -0.9677
                            -26.500  -0.8570   -0.8804  -0.8804   -0.8804   -0.9305   -0.9492    -0.9549
                            -26.000  -0.8419   -0.8643  -0.8805   -0.8805   -0.9169   -0.9362    -0.9518
                            -25.500  -0.8265   -0.8479  -0.8584   -0.8648   -0.9095   -0.9319    -0.9499
                            -25.000  -0.8109   -0.8412  -0.8424   -0.8489   -0.8972   -0.9200    -1.5067
                            -24.500  -0.7952   -0.8352  -0.8263   -0.8752   -0.8927   -1.2202    -1.6624
                            -24.000  -0.7793   -0.8300  -0.8100   -0.8661   -1.1000   -1.6171    -1.7264
                            -23.500  -0.7635   -0.8250  -0.8036   -0.8614   -1.4000   -1.6808    -1.7599
                            -23.000  -0.7700   -0.8175  -0.8258   -0.8587   -1.5555   -1.7146    -1.7817
                            -22.500  -0.7760   -0.8063  -0.8210   -0.8604   -1.6133   -1.7355    -1.7932
                            -22.000  -0.7810   -0.8072  -1.1000   -1.4182   -1.6435   -1.7467    -1.7987
                            -21.500  -0.7850   -0.8107  -1.3721   -1.4895   -1.6617   -1.7516    -1.7998
                            -21.000  -0.7920   -0.8258  -1.4465   -1.5280   -1.6702   -1.7522    -1.7791
                            -20.500  -0.7939   -1.2223  -1.4829   -1.5503   -1.6734   -1.7477    -1.7491
                            -20.000  -0.8231   -1.3581  -1.5026   -1.5617   -1.6722   -1.7281    -1.7106
                            -19.500  -0.9303   -1.3953  -1.5119   -1.5670   -1.6649   -1.6896    -1.7131
                            -19.000  -1.0403   -1.4142  -1.5150   -1.5671   -1.6534   -1.6458    -1.6371
                            -18.500  -1.2176   -1.4223  -1.5124   -1.5610   -1.6174   -1.6111    -1.6230
                            -18.000  -1.2529   -1.4233  -1.5037   -1.5495   -1.5998   -1.5754    -1.6055
                            -17.500  -1.2691   -1.4173  -1.4892   -1.5333   -1.5205   -1.5579    -1.5864
                            -17.000  -1.2746   -1.4049  -1.4697   -1.5125   -1.4936   -1.5388    -1.5676
                            -16.500  -1.2708   -1.3870  -1.4454   -1.4648   -1.4754   -1.5204    -1.5517
                            -16.000  -1.2843   -1.3759  -1.4236   -1.4049   -1.4569   -1.5052    -1.5355
                            -15.500  -1.2777   -1.3817  -1.3431   -1.3861   -1.4409   -1.4828    -1.4988
                            -15.000  -1.2603   -1.3040  -1.3261   -1.3717   -1.4289   -1.4450    -1.4584
                            -14.500  -1.2386   -1.2818  -1.3154   -1.3475   -1.3922   -1.4060    -1.4153
                            -14.000  -1.2159   -1.2618  -1.2979   -1.3154   -1.3503   -1.3640    -1.3711
                            -13.500  -1.1695   -1.2395  -1.2726   -1.2788   -1.3057   -1.3186    -1.3255
                            -13.000  -1.1535   -1.2070  -1.2230   -1.2378   -1.2591   -1.2708    -1.2778
                            -12.500  -1.1269   -1.1688  -1.1801   -1.1937   -1.2033   -1.2216    -1.2280
                            -12.000  -1.0926   -1.1271  -1.1379   -1.1467   -1.1629   -1.1715    -1.1772
                            -11.500  -1.0523   -1.0829  -1.0928   -1.1007   -1.1141   -1.1205    -1.1255
                            -11.000  -1.0074   -1.0355  -1.0450   -1.0525   -1.0634   -1.0696    -1.0733
                            -10.500  -0.9634   -0.9872  -0.9948   -1.0026   -1.0125   -1.0174    -1.0211
                            -10.000  -0.9152   -0.9365  -0.9445   -0.9505   -0.9608   -0.9651    -0.9677
                             -9.500  -0.8682   -0.8861  -0.8921   -0.8984   -0.9078   -0.9120    -0.9144
                             -9.000  -0.8178   -0.8343  -0.8530   -0.8450   -0.8534   -0.8579    -0.8602
                             -8.500  -0.7680   -0.7819  -0.7867   -0.7913   -0.7990   -0.8027    -0.8054
                             -8.000  -0.7167   -0.7286  -0.7332   -0.7370   -0.7437   -0.7473    -0.7494
                             -7.500  -0.6642   -0.6751  -0.6791   -0.6826   -0.6885   -0.6914    -0.6936
                             -7.000  -0.6105   -0.6206  -0.6244   -0.6274   -0.6326   -0.6353    -0.6371
                             -6.500  -0.5566   -0.5656  -0.5829   -0.5724   -0.5768   -0.5791    -0.5806
                             -6.000  -0.5026   -0.5102  -0.5129   -0.5158   -0.5202   -0.5225    -0.5241
                             -5.500  -0.4479   -0.4543  -0.4569   -0.4593   -0.4634   -0.4654    -0.4670
                             -5.000  -0.3928   -0.3982  -0.4004   -0.4023   -0.4060   -0.4082    -0.4097
                             -4.500  -0.3375   -0.3419  -0.3436   -0.3456   -0.3488   -0.3506    -0.3519
                             -4.000  -0.2857   -0.2857  -0.2870   -0.2884   -0.2912   -0.2930    -0.2943
                             -3.500  -0.2309   -0.2306  -0.2309   -0.2316   -0.2337   -0.2351    -0.2362
                             -3.000  -0.1808   -0.1756  -0.1752   -0.1753   -0.1763   -0.1774    -0.1783
                             -2.500  -0.1293   -0.1221  -0.1195   -0.1190   -0.1192   -0.1200    -0.1209
                             -2.000  -0.0720   -0.0683  -0.0654   -0.0628   -0.0622   -0.0628    -0.0636
                             -1.500  -0.0135   -0.0132  -0.0105   -0.0074   -0.0050   -0.0057    -0.0067
                             -1.000   0.0446    0.0450   0.0455    0.0480    0.0519    0.0517     0.0503
                             -0.500   0.1034    0.1034   0.1037    0.1043    0.1083    0.1084     0.1072
                             0.000    0.1616    0.1621   0.1620    0.1621    0.1647    0.1649     0.1640
                             0.500    0.2200    0.2203   0.2204    0.2205    0.2198    0.2200     0.2196
                             1.000    0.2782    0.2790   0.2789    0.2789    0.2770    0.2749     0.2743
                             1.500    0.3363    0.3374   0.3372    0.3370    0.3334    0.3289     0.3296
                             2.000    0.3942    0.3954   0.3951    0.3941    0.3859    0.3848     0.3847
                             2.500    0.4523    0.4527   0.4521    0.4483    0.4415    0.4408     0.4413
                             3.000    0.5092    0.5089   0.5051    0.4987    0.4966    0.4974     0.4982
                             3.500    0.5655    0.5612   0.5542    0.5531    0.5523    0.5537     0.5547
                             4.000    0.6203    0.6079   0.6062    0.6059    0.6086    0.6097     0.6108
                             4.500    0.6644    0.6581   0.6592    0.6610    0.6638    0.6649     0.6661
                             5.000    0.7097    0.7114   0.7132    0.7151    0.7170    0.7196     0.7216
                             5.500    0.7582    0.7639   0.7655    0.7665    0.7718    0.7752     0.7773
                             6.000    0.8079    0.8127   0.8153    0.8191    0.8265    0.8302     0.8328
                             6.500    0.8533    0.8624   0.8676    0.8724    0.8805    0.8848     0.8875
                             7.000    0.8988    0.9132   0.9194    0.9250    0.9342    0.9389     0.9419
                             7.500    0.9462    0.9636   0.9702    0.9765    0.9871    0.9926     0.9960
                             8.000    0.9916    1.0126   1.0203    1.0275    1.0398    1.0456     1.0496
                             8.500    1.0304    1.0604   1.0816    1.0776    1.0913    1.0977     1.1001
                             9.000    1.0781    1.1065   1.1172    1.1272    1.1417    1.1461     1.1507
                             9.500    1.1100    1.1517   1.1641    1.1728    1.1873    1.1958     1.2017
                             10.000   1.1445    1.1941   1.2079    1.2183    1.2345    1.2447     1.2504
                             10.500   1.1703    1.2294   1.2423    1.2600    1.2788    1.2788     1.2993
                             11.000   1.2170    1.2500   1.2662    1.2934    1.3226    1.3226     1.3468
                             11.500   1.2513    1.2696   1.2902    1.3202    1.3638    1.3812     1.3927
                             12.000   1.2735    1.3030   1.3179    1.3469    1.3950    1.4230     1.4367
                             12.500   1.2990    1.3372   1.3435    1.3739    1.4192    1.4553     1.4781
                             13.000   1.3227    1.3650   1.3937    1.4003    1.4449    1.4796     1.5072
                             13.500   1.3432    1.3910   1.4297    1.4738    1.4800    1.5063     1.5319
                             14.000   1.3648    1.4202   1.4678    1.5047    1.4954    1.5335     1.5575
                             14.500   1.3856    1.4497   1.5000    1.5372    1.5182    1.5611     1.5866
                             15.000   1.4029    1.4762   1.5282    1.5666    1.5948    1.5867     1.6143
                             15.500   1.4171    1.4981   1.5527    1.5930    1.6054    1.6108     1.6402
                             16.000   1.4273    1.5162   1.5744    1.6159    1.6551    1.6848     1.6647
                             16.500   1.4341    1.5302   1.5922    1.6363    1.6750    1.6866     1.6878
                             17.000   1.4363    1.5406   1.6065    1.6534    1.6876    1.7324     1.7232
                             17.500   1.4337    1.5474   1.6185    1.6666    1.7050    1.7798     1.7556
                             18.000   1.4258    1.5496   1.6259    1.6780    1.7207    1.8136     1.7920
                             18.500   1.4116    1.5464   1.6310    1.6845    1.7347    1.8315     1.8326
                             19.000   1.3898    1.5376   1.6304    1.6892    1.7434    1.8464     1.8710
                             19.500   1.3591    1.5216   1.6256    1.6877    1.7502    1.8586     1.9019
                             20.000   1.3150    1.4966   1.6150    1.6824    1.7518    1.8693     1.9149
                             20.500   1.2531    1.4586   1.5976    1.6719    1.7511    1.8765     1.9254
                             21.000   1.1746    1.4099   1.5715    1.6546    1.7429    1.8800     1.9341
                             21.500   1.1108    1.3357   1.5316    1.6287    1.7301    1.8821     1.9364
                             22.000   1.0361    1.1959   1.4760    1.5931    1.7099    1.8768     1.9385
                             22.500   0.9867    1.0850   1.4091    1.5406    1.6811    1.8692     1.9341
                             23.000   0.9786    1.0450   1.2949    1.4752    1.6335    1.8568     1.9282
                             23.500   0.9790    1.0375   1.1414    1.3923    1.5618    1.8363     1.9143
                             24.000   0.9829    1.0308   1.0759    1.2697    1.4000    1.8070     1.8949
                             24.500   0.9892    1.0259   1.0570    1.1269    1.1269    1.7689     1.8697
                             25.000   0.9960    1.0108   1.0509    1.0760    1.0912    1.7134     1.8373
                             25.500   1.0026    1.0000   1.0464    1.0683    1.0735    1.6233     1.7905
                             26.000   1.0023    0.9984   1.0129    1.0667    1.0686    1.5269     1.7231
                             26.500   1.0121    1.0127   1.0254    1.0671    1.0649    1.3429     1.6233
                             27.000   1.0242    1.0242   1.0292    1.0674    1.0700    1.2282     1.5282
                             27.500   1.0365    1.0365   1.0463    1.0629    1.0800    1.1008     1.3872
                             28.000   1.0486    1.0486   1.0634    1.0829    1.1029    1.1100     1.1729
                             28.500   1.0606    1.0606   1.0834    1.0976    1.1250    1.1290     1.1450
                             29.000   1.0723    1.0723   1.1020    1.1130    1.1325    1.1696     1.1696
                             29.500   1.0838    1.0838   1.1182    1.1275    1.1475    1.1775     1.1726
                             30.000   1.0952    1.0952   1.1329    1.1408    1.1567    1.1831     1.1831
                             31.000   1.1171    1.1171   1.1612    1.1660    1.1773    1.1919     1.1975
                             32.000   1.1378    1.1378   1.1866    1.1894    1.1994    1.2085     1.2175
                             33.000   1.1571    1.1571   1.2096    1.2317    1.2317    1.2283     1.2317
                             34.000   1.1750    1.1750   1.2306    1.2496    1.2496    1.2496     1.2496
                             35.000   1.1915    1.1915   1.2497    1.2659    1.2659    1.2659     1.2659
                             36.000   1.2066    1.2066   1.2671    1.2808    1.2808    1.2808     1.2808
                             37.000   1.2204    1.2204   1.2858    1.2944    1.2944    1.2944     1.2944
                             38.000   1.2333    1.2333   1.3071    1.3071    1.3071    1.3071     1.3071
                             39.000   1.2441    1.2441   1.3224    1.3224    1.3177    1.3177     1.3177
                             40.000   1.2532    1.2532   1.3266    1.3266    1.3266    1.3266     1.3266
                             41.000   1.2605    1.2605   1.3337    1.3337    1.3337    1.3337     1.3337
                             42.000   1.2661    1.2661   1.339     1.339     1.339     1.339      1.339
                             60.000   0.6       0.6      0.6       0.6       0.6       0.6        0.6
                             90.000   0.027     0.027    0.027     0.027     0.027     0.027      0.027
                             120.00   0.046     0.046    0.046     0.046     0.046     0.046      0.046
                             150.00   0.238     0.238    0.238     0.238     0.238     0.238      0.238
                             180.00   -0.168    -0.168  -0.168     -0.168   -0.168    -0.168     -0.168
                          </tableData>
                      </table>
                </product>
            </function>
            
            <function name="aero/coefficient/dCLflap">
                <description>Delta_Lift_due_to_flaps</description>
                <product>
                    <property>aero/thrust-qbar_psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <value>0.3000</value>
                </product>
            </function>
            
            <function name="aero/coefficient/CLde">
                <description>Lift_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/thrust-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>-0.10</value>
                    <!-- Asymmetric stall -->
                    <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">velocities/vc-kts</independentVar>
                        <tableData>
                                 0    90   140   180
                            -35  1    8     2    1
                            -10  1    14    4    2
                            -8   1    1     1    1
                            10.2 1    1     1    1
                            14   1    2.5   2    1.5
                            15   1    22.5  17.5 5
                            25   1    25    20   3
                            35   1    12    9    2
                        </tableData> 
                    </table>
                    <table>
                        <independentVar lookup="row">/gear/gear[0]/wow</independentVar>
                        <independentVar lookup="column">/gear/gear[1]/wow</independentVar>
                        <tableData>
                                0   1
                            0   1   0 
                            1   0   0
                        </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>-0.4000</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>0.07</value>
                    <!-- Asymmetric stall -->
                    <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">velocities/vc-kts</independentVar>
                        <tableData>
                                 0    90   140   180
                            -35  1    8     2    1
                            -10  1    14    4    2
                            -8   1    1     1    1
                            10.2 1    1     1    1
                            14   1    2.5   2    1.5
                            15   1    20    18   4
                            25   1    20    18   3
                            35   1    12    8    2
                        </tableData>
                    </table> 
                    <table>
                        <independentVar lookup="row">/gear/gear[0]/wow</independentVar>
                        <independentVar lookup="column">/gear/gear[1]/wow</independentVar>
                        <tableData>
                                0   1
                            0   1   0 
                            1   0   0
                        </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>
                    <sum>
                       <property>fcs/left-aileron-pos-rad</property>
                       <value>0.02</value>
                    </sum>
                    <table>
                        <independentVar>velocities/mach</independentVar>
                        <tableData>
                            0.0000        0.1200
                            1.0000        0.100
                        </tableData>
                    </table>
                    <!-- Asymmetric stall -->
                    <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <tableData>
                        -35    0.3
                        -9     0.3
                        -8     1
                        10     1
                        11     0.3
                        35     0.3
                        </tableData>
                    </table>
                 </product>
            </function>
            
            <function name="aero/coefficient/Cldr">
                <description>Roll_moment_due_to_rudder</description>
                <product>
                    <property>aero/thrust-qbar_psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.003</value>
                </product>
            </function>

           <!--
               Create roll moment with a tendancy
               to drop the left wing at stall.
               This will help to induce a spin.

               The positive value at aero/alpha-deg = 10.35
               is to simulate actual behavior.  The NACA
               test report on stall behavior says that
               initially it will drop the right wing and then
               roll to the left as the stall deepens.
            -->
           <function name="aero/coefficient/Clalpha">
                <description>roll_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/Re</independentVar>
                        <tableData>
                                          2500000  5000000  10000000   20000000
                               -33.0      0.0     -0.005   -0.0025    -0.000025
                                -9.0      0.0     -0.00025 -0.000125  -0.00000125
                                 0.0      0.0      0.0      0.0        0.0
                                14        0.0      0.0      0.0        0.0
                                14.15     0.0      0.0025   0.00125    0.00000125
                                14.3      0.0     -0.00025 -0.000125  -0.000000125
                                34.5      0.0     -0.0005  -0.00025   -0.00000025
                        </tableData>
                    </table>
                    <table>
                        <independentVar lookup="row">/gear/gear[0]/wow</independentVar>
                        <independentVar lookup="column">/gear/gear[1]/wow</independentVar>
                        <tableData>
                                0   1
                            0   1   0 
                            1   0   0
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>

        <axis name="PITCH">

            <!-- make it nose heavy when gear and/or flaps are extended --> 

            <function name="aero/coefficient/Cmflap">
                <description>Pitch_moment_due_to_flaps</description>
                <product>
                    <property>aero/thrust-qbar_psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/flap-pos-norm</property>
                    <value>-0.0250</value>
                </product>
            </function>

            <function name="aero/coefficient/Cmgear">
                <description>Pitch_moment_due_to_gear</description>
                <product>
                    <property>aero/thrust-qbar_psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>gear/gear-pos-norm</property>
                    <value>-0.0070</value>
                </product>
            </function>

            <function name="aero/coefficient/Cmalpha-wing">
                <description>Pitch_moment_due_to_alpha</description>
                  <product>
                      <property>aero/qbar-psf</property>
                      <property>metrics/Sw-sqft</property>
                      <property>metrics/cbarw-ft</property>
                      <!--
                          actual data from http://www.worldofkrauss.com/foils/getpolar/1085.dat 
                          from -15 to 15 degrees - other data is extrapolated.
                          Data has been hand smoothed.
                      -->
                      <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <tableData> 
                          -90.0        0.58700
                          -80.0        0.51700
                          -70.0        0.44700
                          -60.0        0.37700
                          -50.0        0.30700
                          -40.0        0.23700
                          -30.0        0.16700
                          -20.0        0.09700
                          -15.0        0.06100
                          -14.5        0.05800
                          -14.0        0.05500
                          -13.5        0.05200
                          -13.0        0.04800
                          -12.5        0.04500
                          -12.0        0.04200
                          -11.5        0.03900
                          -11.0        0.03500
                          -10.5        0.03200
                          -10.0        0.02800
                          -9.5         0.02500
                          -9.0         0.02200
                          -8.5         0.01800
                          -8.0         0.01500
                          -7.5         0.01100
                          -7.0         0.00800
                          -6.5         0.00500
                          -6.0         0.00200
                          -5.5        -0.00160
                          -5.0        -0.00500
                          -4.5        -0.00800
                          -4.0        -0.01200
                          -3.5        -0.01550
                          -3.0        -0.01850
                          -2.5        -0.02150
                          -2.0        -0.02500
                          -1.5        -0.02800
                          -1.0        -0.03100
                          -0.5        -0.03500
                          0.0         -0.03800
                          0.5         -0.04100
                          1.0         -0.04350
                          1.5         -0.04600
                          2.0         -0.04900
                          2.5         -0.05200
                          3.0         -0.05500
                          3.5         -0.05700
                          4.0         -0.06000
                          4.5         -0.06300
                          5.0         -0.06500
                          5.5         -0.06750
                          6.0         -0.07050
                          6.5         -0.07350
                          7.0         -0.07600
                          7.5         -0.07900
                          8.0         -0.08200
                          8.5         -0.08600
                          9.0         -0.09100
                          9.5         -0.09700
                          10.0        -0.10400
                          10.5        -0.11400
                          11.0        -0.12300
                          11.5        -0.13000
                          12.0        -0.13600
                          12.5        -0.13900
                          13.0        -0.14200
                          13.5        -0.14400
                          14.0        -0.14600
                          14.5        -0.14700
                          15.0        -0.14800
                          16.0        -0.15000
                          17.0        -0.16000
                          18.0        -0.17000
                          19.0        -0.18000
                          20.0        -0.19000
                          30.0        -0.25300
                          40.0        -0.32300
                          50.0        -0.39300
                          60.0        -0.46300
                          70.0        -0.53300
                          80.0        -0.60300
                          90.0        -0.67300
                      </tableData>
                    </table>
                </product>
            </function>

            <!--<function name="aero/coefficient/Cmbuffet-and-stall">
                <description>Pitch_moment_due_to_stall-buffet</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <sum>
                        <property>systems/alpha_buffet/sine_wave</property>
                        <product>
                          <value>0.005</value>
                          <property>systems/alpha_buffet/strength</property>
                        </product>
                    </sum>
                    <property>systems/alpha_buffet/strength</property>
                    <value>1.0</value>
                </product>
            </function>-->

            <function name="aero/coefficient/Cm-mach-porpoise">
                <description>Pitch_moment_due_mach_porpoise</description>
                <product>
                    <property>/fdm/jsbsim/systems/compressibility/enabled</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>/fdm/jsbsim/systems/compressibility/sine_wave</property>
                    <property>/fdm/jsbsim/systems/compressibility/strength</property>
                    <value>0.1</value>
                </product>
            </function>

            <function name="aero/coefficient/Cm-mach-tuck">
                <description>Pitch_moment_due_mach</description>
                <product>
                    <property>/fdm/jsbsim/systems/compressibility/enabled</property>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <table>  <!-- control reversal -->
                        <independentVar>/fdm/jsbsim/velocities/mach</independentVar>
                        <tableData>
                            0.0000        0.0
                            0.746         0.0
                            0.775         -0.05
                            1.0000        -0.2
                        </tableData>
                    </table>
                </product>
            </function>

            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator</description>
                <product>
                    <property>aero/thrust-qbar_psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/elevator-pos-rad</property>
                    <table>
                        <independentVar>/fdm/jsbsim/velocities/mach</independentVar>
                        <tableData>
                            0.0000        -0.90000
                            0.66          -.6
                            0.74          -0.4 
                            1.0000        -0.05
                        </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>-10.0000</value>
                </product>
            </function>

            <function name="aero/coefficient/Cmht">
                <description>Pitch_moment_due_to_alpha_horiz_tail</description>
                <product>
                    <property>aero/thrust-qbar_psf</property>
                    <property>metrics/Sh-sqft</property>
                    <property>metrics/lh-ft</property>
					<property>aero/pitch-moment-damping-factor</property>
                    <value> -0.6 </value>
                    <table>
                      <independentVar lookup="row">aero/alpha-deg</independentVar>
                      <tableData>					                  
                          -178.25     0.0000
                          -168.25     0.7800
                          -158.25     0.6700
                          -148.25     0.6200
                          -138.25     0.8900
                          -128.25     0.8900
                          -118.25     0.7400
                          -108.25     0.5000
                          -98.25      0.2300
                          -88.25      -0.0500
                          -78.25      -0.3650
                          -68.25      -0.6300
                          -58.25      -0.8900
                          -48.25      -1.0900
                          -38.25      -1.0800
                          -28.25      -0.9200
                          -18.25      -0.6800
                          -17.25      -0.6500
                          -16.25      -0.6200
                          -15.25      -0.6000
                          -14.25      -0.6000
                          -13.25      -0.6800
                          -12.25      -0.7800
                          -11.25      -0.8700
                          -10.25      -0.9500
                          -9.25       -1.0000
                          -8.25       -0.9800
                          -7.25       -0.9300
                          -6.25       -0.8700
                          -5.25       -0.7900
                          -4.25       -0.7000
                          -3.25       -0.6000
                          -2.25       -0.5000
                          -1.25       -0.3800
                          -0.25       -0.2600
                           0.75       -0.1300
                          1.75        0
                          3.25        0.13
                          4.75        0.26
                          6.25        0.38
                          7.75        0.5
                          9.25        0.6
                          10.75       0.7
                          12.25       0.79
                          13.75       0.87
                          15.25       0.93
                          16.75       1
                          18.625      0.95
                          19.5625     0.78
                          21.4375     0.68
                          22.375      0.6
                          23.3125     0.6
                          24.25       0.62
                          25.1875     0.65
                          26.125      0.68
                          35.5        0.92
                          44.875      1.08
                          54.25       1.09
                          63.625      0.89
                          73          0.63
                          82.375      0.365
                          91.75       0.05
                          101.75      -0.23
                          111.75      -0.5
                          121.75      -0.74
                          131.75      -0.89
                          141.75      -0.89
                          151.75      -0.62
                          161.75      -0.67
                          171.75      -0.78
                          181.75      0
                      </tableData>
                  </table>
                </product>
            </function>

        </axis>

        <axis name="YAW">
            <function name="aero/coefficient/Cnb">
                <description>Yaw_moment_due_to_beta</description>
                <product>
                    <property>aero/thrust-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/Cnspw">
                <description>Yaw_moment_due_to_spiraling_propwash</description>
                <product>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>propulsion/engine/thrust-lbs</property>
                    <value>-0.00002</value>
                    <table>
                        <independentVar lookup="row">/velocities/airspeed-kt</independentVar>
                        <tableData>
                            0    1
                            140  1
                            190  0
                        </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>-0.1500</value>
                </product>
            </function>
            
            <function name="aero/coefficient/Cndr">
                <description>Yaw_moment_due_to_rudder</description>
                <product>
                    <property>aero/thrust-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>-0.0030</value>
                </product>
            </function>

            <!--
               Create YAW to help drop a wing at stall.
               This will help to induce a spin or a snap
               roll depending on how fast the stall entry
               speed is.
               Which wing is dropped and how hard it
               drops depends on the beta angle.
            -->
            
           <function name="aero/coefficient/Cnalphabeta">
                <description>Yaw_moment_due_to_alpha-beta</description>
                <product>
                    <value> -1.0 </value>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <table>
                        <independentVar lookup="row">aero/alpha-deg</independentVar>
                        <independentVar lookup="column">aero/beta-deg</independentVar>
                        <independentVar lookup="table">aero/Re</independentVar>
                        <tableData breakPoint="2500000">
                                     -30     -5      -2      2.5       6      32
                               -14.5  0.0  0.05      0.03    -0.03     -0.05    0.0
                               -10.0  0.0  0.05      0.03    -0.03     -0.05    0.0
                                -9.5  0.0  0.05      0.03    -0.03     -0.05    0.0
                                -9.0  0.0  0.05      0.03    -0.03     -0.05    0.0
                                -8.5  0.0  0.05      0.03    -0.03     -0.05    0.0
                                -8.0  0.0  0.05      0.03    -0.03     -0.05    0.0
                                -7.0  0.0  0.0       0.0      0.0      0.0      0.0
                                 0.0  0.0  0.0       0.0      0.0      0.0      0.0
                                10.0  0.0  0.0       0.0      0.0      0.0      0.0
                                10.6  0.0  0.001     0.005   -0.005   -0.001    0.0
                                11.2  0.0  0.0015    0.006   -0.006   -0.0015   0.0
                                11.5  0.0  0.0025    0.008   -0.008   -0.0025   0.0
                                12.0  0.0  0.0035    0.01    -0.01    -0.0035   0.0
                                12.2  0.0  0.005     0.012   -0.012   -0.005    0.0
                                12.5  0.0  0.00625   0.013   -0.013   -0.00625  0.0
                                14.5  0.0  0.0075    0.015   -0.015   -0.0075   0.0
                                25.0  0.0  0.00125   0.005   -0.005   -0.00125  0.0
                        </tableData>
                        <tableData breakPoint="5000000">
                                     -30    -5       -2        2.5          6          32
                               -14.5 0.0  0.05      0.03      -0.03       -0.05        0.0
                               -10.0 0.0  0.05      0.03      -0.03       -0.05        0.0
                                -9.5 0.0  0.05      0.03      -0.03       -0.05        0.0
                                -9.0 0.0  0.05      0.03      -0.03       -0.05        0.0
                                -8.5 0.0  0.05      0.03      -0.03       -0.05        0.0
                                -8.0 0.0  0.005     0.003     -0.003      -0.005       0.0
                                -7.0 0.0  0.0       0.0        0.0         0.0         0.0
                                 0.0 0.0  0.0       0.0        0.0         0.0         0.0
                                10.0 0.0  0.0       0.0        0.0         0.0         0.0
                                10.6 0.0  0.005     0.01      -0.01       -0.005       0.0
                                11.2 0.0  0.015     0.01      -0.01       -0.015       0.0
                                11.5 0.0  0.02      0.015     -0.015      -0.02        0.0
                                12.0 0.0  0.025     0.02      -0.02       -0.025       0.0
                                12.2 0.0  0.03      0.023     -0.023      -0.03        0.0
                                12.5 0.0  0.04      0.026     -0.026      -0.04        0.0
                                14.5 0.0  0.05      0.03      -0.03       -0.05        0.0
                                25.0 0.0  0.02      0.01      -0.01       -0.02        0.0
                        </tableData>
                        <tableData breakPoint="10000000">
                                        -30    -5      -2      2.5         6         32
                               -14.5    0.0  0.05     0.03    -0.03      -0.05       0.0
                               -10.0    0.0  0.05     0.03    -0.03      -0.05       0.0
                                -9.5    0.0  0.05     0.03    -0.03      -0.05       0.0
                                -9.0    0.0  0.05     0.03    -0.03      -0.05       0.0
                                -8.5    0.0  0.02     0.01    -0.01      -0.02       0.0
                                -8.0    0.0  0.005    0.003   -0.003     -0.005      0.0
                                -7.0    0.0  0.0      0.0      0.0        0.0        0.0
                                 0.0    0.0  0.0      0.0      0.0        0.0        0.0
                                10.0    0.0  0.0      0.0      0.0        0.0        0.0
                                10.6    0.0  0.002    0.006   -0.006     -0.002      0.0
                                11.2    0.0  0.005    0.005   -0.005     -0.005      0.0
                                11.5    0.0  0.01     0.01    -0.01      -0.01       0.0
                                12.0    0.0  0.015    0.015   -0.015     -0.015      0.0
                                12.2    0.0  0.03     0.02    -0.02      -0.03       0.0
                                12.5    0.0  0.035    0.025   -0.025     -0.035      0.0
                                14.5    0.0  0.04     0.03    -0.03      -0.04       0.0
                                25.0    0.0  0.02     0.01    -0.01      -0.02       0.0
                        </tableData>
                        <tableData breakPoint="20000000">
                                        -30    -5        -2       2.5       6        32
                               -14.5    0.0    0.05     0.03    -0.03     -0.05      0.0
                               -10.0    0.0    0.05     0.03    -0.03     -0.05      0.0
                                -9.5    0.0    0.05     0.03    -0.03     -0.05      0.0
                                -9.0    0.0    0.02     0.01    -0.01     -0.02      0.0
                                -8.5    0.0    0.005    0.003   -0.003    -0.005     0.0
                                -8.0    0.0    0.002    0.001   -0.001    -0.002     0.0
                                -7.0    0.0    0.0      0.0      0.0       0.0       0.0
                                 0.0    0.0    0.0      0.0      0.0       0.0       0.0
                                10.0    0.0    0.0      0.0      0.0       0.0       0.0
                                10.6    0.0    0.0      0.0      0.0       0.0       0.0
                                11.2    0.0    0.0      0.0      0.0       0.0       0.0
                                11.5    0.0    0.0      0.0      0.0       0.0       0.0
                                12.0    0.0    0.01     0.01    -0.01     -0.01      0.0
                                12.2    0.0    0.02     0.016   -0.016    -0.02      0.0
                                12.5    0.0    0.03     0.023   -0.023    -0.03      0.0
                                14.5    0.0    0.05     0.03    -0.03     -0.05      0.0
                                25.0    0.0    0.02     0.01    -0.01     -0.02      0.0
                        </tableData>
                        <tableData breakPoint="30000000">
                                       -30     -5          -2      2.5     6       32
                               -14.5   0.0    0.05       0.03    -0.03   -0.05     0.0
                               -10.0   0.0    0.05       0.03    -0.03   -0.05     0.0
                                -9.5   0.0    0.02       0.01    -0.01   -0.02     0.0
                                -9.0   0.0    0.005      0.003   -0.003  -0.005    0.0
                                -8.5   0.0    0.002      0.001   -0.001  -0.002    0.0
                                -8.0   0.0    0.0        0.0      0.0     0.0      0.0
                                -7.0   0.0    0.0        0.0      0.0     0.0      0.0
                                 0.0   0.0    0.0        0.0      0.0     0.0      0.0
                                10.0   0.0    0.0        0.0      0.0     0.0      0.0
                                10.6   0.0    0.0        0.0      0.0     0.0      0.0
                                11.2   0.0    0.0        0.0      0.0     0.0      0.0
                                11.5   0.0    0.0        0.0      0.0     0.0      0.0
                                12.0   0.0    0.0        0.0      0.0     0.0      0.0
                                12.2   0.0    0.01       0.01    -0.01   -0.01     0.0
                                12.5   0.0    0.03       0.02    -0.02   -0.03     0.0
                                14.5   0.0    0.05       0.03    -0.03   -0.05     0.0
                                25.0   0.0    0.02       0.01    -0.01   -0.02     0.0
                        </tableData>
                        <tableData breakPoint="40000000">
                                         -30     -5       -2       2.5       6      32
                               -14.5     0.0    0.05     0.03    -0.03     -0.05    0.0
                               -10.0     0.0    0.05     0.03    -0.03     -0.05    0.0
                                -9.5     0.0    0.02     0.01    -0.01     -0.02    0.0
                                -9.0     0.0    0.005    0.003   -0.003    -0.005   0.0
                                -8.5     0.0    0.002    0.001   -0.001    -0.002   0.0
                                -8.0     0.0    0.0      0.0      0.0       0.0     0.0
                                -7.0     0.0    0.0      0.0      0.0       0.0     0.0
                                 0.0     0.0    0.0      0.0      0.0       0.0     0.0
                                10.0     0.0    0.0      0.0      0.0       0.0     0.0
                                10.6     0.0    0.0      0.0      0.0       0.0     0.0
                                11.2     0.0    0.0      0.0      0.0       0.0     0.0
                                11.5     0.0    0.0      0.0      0.0       0.0     0.0
                                12.0     0.0    0.0      0.0      0.0       0.0     0.0
                                12.2     0.0    0.0      0.0      0.0       0.0     0.0
                                12.5     0.0    0.03     0.02    -0.02     -0.03    0.0
                                14.5     0.0    0.05     0.03    -0.03     -0.05    0.0
                                25.0     0.0    0.02     0.01    -0.01     -0.02    0.0
                        </tableData>
                    </table>
                </product>
            </function>
        </axis>
    </aerodynamics>

</fdm_config>