<?xml version="1.0"?>
<?xml-stylesheet href="http://jsbsim.sourceforge.net/JSBSim.xsl" type="text/xsl"?>
<fdm_config name="a380" version="2.0" release="BETA"
 xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
 xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

<!-- 
     This is the Airbus A380 double-deck wide body subsonic general passenger transport aircraft.
     
     Modification History:
     When	Who		What
     2007	ICunningram	Initial
     2008	KAmpere		update
     2008	FDalvi		update
     APR-2009	SHamilton	update
     Jun-2010	SHamilton	tweak high-lift devices to match CLmax
-->

    <fileheader>
        <author>Cunningham, Ampere, Hamilton, et al</author>
        <filecreationdate> Creation Date </filecreationdate>
        <version>V1.0.3</version>
        <description>Models an A380</description>
    </fileheader>

    <metrics>
        <!-- wingarea unit="FT2"> 8934.95 </wingarea>
        <wingspan unit="FT"> 261.82 </wingspan>
        <chord unit="FT"> 34.13 </chord>
        <htailarea unit="FT2"> 2233.74 </htailarea>
        <htailarm unit="FT"> 102.66 </htailarm>
        <vtailarea unit="FT2"> 1786.99 </vtailarea>
        <vtailarm unit="FT"> 0 </vtailarm -->
	<wingarea  unit="FT2"> 9096.43 </wingarea>
        <wingspan  unit="FT" >  261.82 </wingspan>
        <wing_incidence>          2.00 </wing_incidence>
        <!-- chord     unit="FT" >   33.5 </chord -->
        <chord     unit="FT" >   34.88 </chord>
        <htailarea unit="FT2"> 2274.11 </htailarea>
        <htailarm  unit="FT" >  107.78 </htailarm>
        <vtailarea unit="FT2"> 1819.29 </vtailarea>
        <vtailarm  unit="FT" >  107.78 </vtailarm>

        <location name="AERORP" unit="IN">
            <x> 1580.8 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
        <location name="EYEPOINT" unit="IN">
            <x> 201.2 </x>
            <y> -32 </y>
            <z> 80 </z>
        </location>
        <location name="VRP" unit="M">
            <x> 30.0 </x>
            <y> 0 </y>
            <z> 0 </z>
        </location>
    </metrics>

    <mass_balance>
        <!-- ixx unit="SLUG*FT2"> 9.87831e+07 </ixx>
        <iyy unit="SLUG*FT2"> 9.33213e+07 </iyy>
        <izz unit="SLUG*FT2"> 1.95326e+08 </izz>
        <ixy unit="SLUG*FT2"> 0 </ixy>
        <ixz unit="SLUG*FT2"> 0 </ixz>
        <iyz unit="SLUG*FT2"> 0 </iyz>
        <emptywt unit="LBS"> 725004 </emptywt>
	        <location name="CG" unit="IN">
            <x> 1580.8 </x>
            <y> 0 </y>
            <z> -71.9 </z>
        </location -->
	<ixx unit="SLUG*FT2">  40378502 </ixx>
        <iyy unit="SLUG*FT2">  38145914 </iyy>
        <izz unit="SLUG*FT2">  79841172 </izz>
        <emptywt unit="LBS" >    740880 </emptywt>
        <location name="CG" unit="M">
          <!-- x> 1580.79 </x>
          <y>   0.00 </y>
          <z> -71.85 </z -->
	  <x> 40.152066 </x>
	  <y> 0.0000 </y>
	  <z> -5.52 </z>
        </location>
	<pointmass name="pilots" >
          <weight unit="KG">160</weight>
          <location name="crew" unit = "M">
            <x>  4.0710 </x>                      
            <y>  0.0000 </y>                      
            <z> -7.0326 </z>                      
          </location>                           
        </pointmass>                            

        <pointmass name="passenger main" >
          <weight unit="KG">43040</weight>
          <location name="passenger" unit = "M">
            <x>  37.4554 </x>
            <y>  0.0000 </y>
            <z>  -5.7104 </z>
          </location>
        </pointmass>
        <pointmass name="passenger upper" >
          <weight unit="KG">25200</weight>
          <location name="passenger" unit = "M">
            <x>  37.4554 </x>
            <y>  0.0000 </y>
            <z>  -8.3097 </z>
          </location>
        </pointmass>

        <pointmass name="cargo forward" >
          <weight unit="KG">28577</weight>
          <location name="POINTMASS" unit = "M">
            <x>  15.5171 </x>
            <y>  0.0000 </y>
            <z>  -3.7654 </z>
          </location>
        </pointmass>
	
        <pointmass name="cargo aft" >
          <weight unit="KG">20310</weight>
          <location name="POINTMASS" unit = "M">
            <x>  45.6932 </x>
            <y>  0.0000 </y>
            <z>  -4.1767 </z>
	  </location>
        </pointmass>
	<pointmass name="cargo bulk" >
          <weight unit="KG">2515</weight>
          <location name="POINTMASS" unit = "M">
            <x>  52.4356 </x>
            <y>  0.00 </y>
	    <z>  -4.3714 </z>
          </location>
        </pointmass>
    </mass_balance>

    <ground_reactions>
        <contact type="BOGEY" name="Nose Gear">
            <location unit="IN">
                <x> 488.52 </x>
                <y> 0 </y>
                <z> -344.9 </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"> 362502 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 120834 </damping_coeff>
            <max_steer unit="DEG"> 70 </max_steer>
            <brake_group> NOSE </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="Left Main gear">
            <location unit="IN">
                <x> 1644 </x>
                <!-- y> -282.8 </y -->
                <y>278.972441</y>
                <z> -344.9 </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"> 1.20834e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 241668 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>   <!-- was 0.0 -->
            <brake_group> LEFT </brake_group>
            <retractable>1</retractable>
        </contact>
        <contact type="BOGEY" name="Right Main Gear">
            <location unit="IN">
                <x> 1644 </x>
                <!-- y> 282.8 </y -->
                <y>-278.972441</y>
                <z> -344.9 </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"> 1.20834e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 241668 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>   <!-- was 0.0 -->
            <brake_group> RIGHT </brake_group>
            <retractable>1</retractable>
        </contact>
<!--

        <contact type="STRUCTURE" name="ELG">
            <location unit="IN">
                <x> 488,52 </x>
                <y> 0 </y>
                <z> -322.9 </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"> 362502 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 120834 </damping_coeff>
            <max_steer unit="DEG"> 30 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="STRUCTURE" name="EMLG1">
            <location unit="IN">
                <x> 1644 </x>
                <y> -282.8 </y>
                <z> -322.9 </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"> 1.20834e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 241668 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
        <contact type="STRUCTURE" name="EMLG2">
            <location unit="IN">
                <x> 1644 </x>
                <y> 282.8 </y>
                <z> -322.9 </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"> 1.20834e+06 </spring_coeff>
            <damping_coeff unit="LBS/FT/SEC"> 241668 </damping_coeff>
            <max_steer unit="DEG"> 0.0 </max_steer>
            <brake_group> NONE </brake_group>
            <retractable>0</retractable>
        </contact>
-->

    </ground_reactions>
    <propulsion>
        <engine file="TRENT-900">
            <location unit="M">
                <x>  46.9824 </x>
                <y>  26.2467 </y>
		<z>  -3.4 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>0</feed>
	    <feed>4</feed>
	    <feed>6</feed>
	    <feed>10</feed>
	    <feed>8</feed>
            <thruster file="direct">
                <location unit="M">
                    <!-- x> 1580.79 </x>
                    <y> -523.648 </y>
                    <z> -40 </z -->
		    <x> 46.9824 </x>
		    <y> 26.2467 </y>
		    <z> -3.4 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="TRENT-900">
            <location unit="M">
                <x> 38.9500 </x>
                <y> 15.9365 </y>
		<z> -2.55 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>1</feed>
	    <feed>4</feed>
	    <feed>6</feed>
	    <feed>10</feed>
	    <feed>8</feed>
            <thruster file="direct">
                <location unit="M">
                    <!-- x> 1580.79 </x>
                    <y> -523.648 </y>
                    <z> -40 </z -->
		    <x> 38.9500 </x>
		    <y> 15.9365 </y>
		    <z> -2.55 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="TRENT-900">
            <location unit="M">
                <x> 38.9500 </x>
		<y> -15.9365 </y>
		<z> -2.55 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>2</feed>
	    <feed>5</feed>
	    <feed>7</feed>
	    <feed>10</feed>
	    <feed>9</feed>
            <thruster file="direct">
                <location unit="M">
                    <!-- x> 1580.79 </x>
                    <y> 523.648 </y>
                    <z> -40 </z -->
		    <x> 38.9500 </x>
		    <y> -15.9365 </y>
		    <z> -2.55 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        <engine file="TRENT-900">
            <location unit="M">
                <x>  46.9824 </x>
                <y>  -26.2467 </y>
		<z>  -3.4 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>3</feed>
	    <feed>5</feed>
	    <feed>7</feed>
	    <feed>10</feed>
	    <feed>9</feed>
            <thruster file="direct">
                <location unit="M">
                    <!-- x> 1580.79 </x>
                    <y> 523.648 </y>
                    <z> -40 </z -->
		    <x>  46.9824 </x>
                    <y>  -26.2467 </y>
		    <z>  -3.4 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
	
	<!--  APU type -->
      <engine file="APU">
            <location unit="IN">
                <x> 100 </x>
                <y> 0 </y>
                <z> 0 </z>
            </location>
            <orient unit="DEG">
                <roll> 0.0 </roll>
                <pitch> 0 </pitch>
                <yaw> 0 </yaw>
            </orient>
            <feed>1</feed>
	    <feed>4</feed>
            <thruster file="direct">
                <location unit="IN">
                <x> 100 </x>
                <y> 0 </y>
                <z> 0 </z>
                </location>
                <orient unit="DEG">
                    <roll> 0.0 </roll>
                    <pitch> 0.0 </pitch>
                    <yaw> 0.0 </yaw>
                </orient>
            </thruster>
        </engine>
        

    <!-- 
           The A380 has 11 tanks in all. The feed tanks feed each engine with
	   a cross-over valve to the next engine. The sequence for feeding the
	   feed tanks is;
	    1. inner tank -> feed
	    2. mid tank   -> feed
	    3. trim tank  -> feed
	    4. outer tank -> feed
	   The trim tank should be moved to the outer trim tank before approach.
    -->
      <tank type="FUEL">    <!-- feed number 0 -->
            <location unit="M">
                <!-- x> 1580.79 </x>
                <y> 200 </y>
                <z> -71.8539 </z -->
		<x> 48.5306 </x>
		<y> 23.4729 </y>
		<z> -5.01 </z>
            </location>
            <capacity unit="LBS"> 48390 </capacity>
            <contents unit="LBS"> 16775 </contents>
	    <priority>1</priority>
        </tank>
        <tank type="FUEL">    <!-- feed number 1 -->
            <location unit="M">
		<x> 37.4956 </x>
		<y> 7.6904 </y>
		<z> -3.3069 </z>
            </location>
            <capacity unit="LBS"> 50780 </capacity>
            <contents unit="LBS"> 18280 </contents>
	    <priority>1</priority>
        </tank>
        <tank type="FUEL">    <!-- feed number 2 -->
            <location unit="M">
		<x> 37.4956 </x>
		<y> -7.6904 </y>
		<z> -3.3069 </z>
            </location>
            <capacity unit="LBS"> 50780 </capacity>
            <contents unit="LBS"> 18280 </contents>
	    <priority>1</priority>
        </tank>
        <tank type="FUEL">    <!-- feed number 3 -->
            <location unit="M">
		<x> 48.5306 </x>
		<y> -23.4729 </y>
		<z> -5.01 </z>
            </location>
            <capacity unit="LBS"> 48390 </capacity>
            <contents unit="LBS"> 16775 </contents>
	    <priority>1</priority>
        </tank>
	<tank type="FUEL">    <!-- innerL 4 -->
            <location unit="M">
		<x> 42.1149 </x>
		<y> 8.5886 </y>
		<z> -3.3069 </z>
            </location>
            <capacity unit="LBS"> 79850 </capacity>
            <contents unit="LBS"> 17034 </contents>
	    <priority>2</priority>
        </tank>
	<tank type="FUEL">    <!-- innerR 5 -->
            <location unit="M">
		<x> 42.1149 </x>
		<y> -8.5886 </y>
		<z> -3.3069 </z>
            </location>
            <capacity unit="LBS"> 79850 </capacity>
            <contents unit="LBS"> 17034 </contents>
	    <priority>2</priority>
        </tank>
	<tank type="FUEL">    <!-- midL 6 -->
            <location unit="M"> 
		<x> 44.0396 </x>
		<y> 15.0043 </y>
		<z> -4.67 </z>
            </location>
            <capacity unit="LBS"> 63100 </capacity>
            <contents unit="LBS"> 16826 </contents>
	    <priority>3</priority>
        </tank>
	<tank type="FUEL">    <!-- midR 7 -->
            <location unit="M">
		<x> 44.0396 </x>
		<y> -15.0043 </y>
		<z> -4.67 </z>
            </location>
            <capacity unit="LBS"> 63100 </capacity>
            <contents unit="LBS"> 16826 </contents>
	    <priority>3</priority>
        </tank>
	<tank type="FUEL">    <!-- outerL 8 -->
            <location unit="M">
		<x> 52.7169 </x>
		<y> 30.1754 </y>
		<z> -5.28 </z>
            </location>
            <capacity unit="LBS"> 18200 </capacity>
            <contents unit="LBS"> 10434 </contents>
	    <priority>4</priority>
        </tank>
	<tank type="FUEL">    <!-- outerR 9 -->
            <location unit="M">
		<x> 52.7169 </x>
		<y> -30.1754 </y>
		<z> -5.28 </z>
            </location>
            <capacity unit="LBS"> 18200 </capacity>
            <contents unit="LBS"> 10434 </contents>
	    <priority>4</priority>
        </tank>
	<tank type="FUEL">    <!-- trim 10 -->
            <location unit="M">
                <!-- x> 1580.79 </x>
                <y> 0 </y>
                <z> -71.8539 </z -->
		<x> 60.8777 </x>
		<y> 0.0000 </y>
		<z> -7.9141 </z>
            </location>
            <capacity unit="LBS"> 41020 </capacity>
            <contents unit="LBS"> 20000 </contents>
	    <priority>5</priority>
        </tank>
            
	
    </propulsion>

    <system file="pushback"/> 

    <flight_control name="FCS: a380">
     <channel name="All">

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

        <aerosurface_scale name="Elevator Control">
            <input>fcs/pitch-trim-sum</input>
            <range>
                <min>-0.35</min>
                <max>0.3</max>
            </range>
            <output>fcs/elevator-pos-rad</output>
        </aerosurface_scale>

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

        <aerosurface_scale name="Left Aileron Control">
            <input>fcs/roll-trim-sum</input>
            <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>

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

        <scheduled_gain name="Yaw Damper Rate">
            <input>velocities/r-aero-rad_sec</input>
            <table>
                <independentVar>aero/qbar-psf</independentVar>
                <tableData>
                    3.0000	0.0000
                    11.0000	2.0000
                </tableData>
            </table>
        </scheduled_gain>

        <scheduled_gain name="Yaw Damper Beta">
            <input>aero/beta-rad</input>
            <table>
                <independentVar>aero/qbar-psf</independentVar>
                <tableData>
                    3.0000	0.0000
                    11.0000	0.0000
                </tableData>
            </table>
        </scheduled_gain>

        <summer name="Yaw Damper Sum">
            <input>fcs/yaw-damper-beta</input>
            <input>fcs/yaw-damper-rate</input>
            <clipto>
                <min>-0.2000</min>
                <max>0.2000</max>
            </clipto>
        </summer>

        <scheduled_gain name="Yaw Damper Final">
            <input>fcs/yaw-damper-sum</input>
            <table>
                <independentVar>aero/qbar-psf</independentVar>
                <tableData>
                    2.9900	0.0000
                    3.0000	1.0000
                </tableData>
            </table>
        </scheduled_gain>

        <summer name="Rudder Sum">
            <input>fcs/rudder-command-sum</input>
            <input>fcs/yaw-damper-final</input>
            <clipto>
                <min>-1.0000</min>
                <max>1.0000</max>
            </clipto>
        </summer>

        <aerosurface_scale name="Rudder Control">
            <input>fcs/rudder-sum</input>
            <range>
                <min>-0.3500</min>
                <max>0.3500</max>
            </range>
            <output>fcs/rudder-pos-rad</output>
        </aerosurface_scale>

        <kinematic name="Flaps Control">
            <input>fcs/flap-cmd-norm</input>
            <traverse>
                <setting>
                    <position>0.0000</position>
                    <time>3.0000</time>
                </setting>
                <setting>
                    <position>7.3000</position>
                    <time>4.0000</time>
                </setting>
                <setting>
                    <position>15.5000</position>
                    <time>2.0000</time>
                </setting>
                <setting>
                    <position>30.0000</position>
                    <time>4.0000</time>
                </setting>
            </traverse>
            <output>fcs/flap-pos-deg</output>

            <aerosurface_scale name="Flap Position Normalizer">
              <input>fcs/flap-pos-deg</input>
              <domain>
                <min>0</min>  <!-- Flaps actual minimum position -->
                <max>30</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>

        </kinematic>

        <kinematic name="Gear Control">
            <input>gear/gear-cmd-norm</input>
            <traverse>
                <setting>
                    <position>0.0000</position>
                    <time>0.0000</time>
                </setting>
                <setting>
                    <position>1.0000</position>
                    <time>5.0000</time>
                </setting>
            </traverse>
            <output>gear/gear-pos-norm</output>
        </kinematic>

        <kinematic name="Speedbrake Control">
            <input>fcs/speedbrake-cmd-norm</input>
            <traverse>
                <setting>
                    <position>0.0000</position>
                    <time>0.0000</time>
                </setting>
                <setting>
                    <position>1.0000</position>
                    <time>1.0000</time>
                </setting>
            </traverse>
            <output>fcs/speedbrake-pos-norm</output>
        </kinematic>
     </channel>
    </flight_control>
    <aerodynamics>

        <axis name="DRAG">
            <function name="aero/coefficient/CD0">
                <description>Drag_at_zero_lift</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -1.5700	1.5000
                              -0.2600	0.0340
                              0.0000	0.0170
                              0.2600	0.0340
                              1.5700	1.5000
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDi">
                <description>Induced_drag</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>aero/cl-squared</property>
                    <!-- value>0.0420</value -->
                    <value>0.0350</value>
                </product>
            </function>
            <function name="aero/coefficient/CDmach">
                <description>Drag_due_to_mach</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.0000
                              0.7900	0.0000
                              1.1000	0.0230
                              1.8000	0.0150
                          </tableData>
                      </table>
                </product>
            </function>
            
            <!-- function name="aero/coefficient/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/flap-pos-norm</property>
                    <value>0.0550</value>  
                </product>
            </function -->
            <function name="aero/coefficient/CDflap">
                <description>Drag_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                      <independentVar>fcs/flap-cmd-norm</independentVar>
                      <tableData>
                      0.00	0.00
                      0.25	0.00
                      0.53	0.001  <!-- 0.00 -->
                      0.79	0.024   <!-- 0.03 -->
                      1.00	0.038    <!-- 0.05 -->
                      </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/CDgear">
                <description>Drag_due_to_gear</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>gear/gear-pos-norm</property>
                    <value>0.0110</value>
                </product>
            </function>
            <function name="aero/coefficient/CDsb">
                <description>Drag_due_to_speedbrakes</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>0.0170</value>
                </product>
            </function>
            <function name="aero/coefficient/CDbeta">
                <description>Drag_due_to_sideslip</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                      <table>
                          <independentVar>aero/beta-rad</independentVar>
                          <tableData>
                              -1.5700	1.2300
                              -0.2600	0.0500
                              0.0000	0.0000
                              0.2600	0.0500
                              1.5700	1.2300
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/CDde">
                <description>Drag_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/elevator-pos-norm</property>
                    <value>0.0550</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>
                      <table>
                          <independentVar>aero/alpha-rad</independentVar>
                          <tableData>
                              -0.2000	-0.6800
                              0.0000	0.2500
                              0.0400	0.8500
                              0.2300	1.3000
                              0.6000	0.7000
                          </tableData>
                          <!-- tableData>
                              -0.2000	-0.6800
                              0.0000	0.3000
                              0.2300	1.2000
                              0.6000	0.7000
                          </tableData -->
                          <!-- 0.0000 0.2000
                               0.2300 1.2000
                               0.6000 0.6000  -->
                      </table>
                </product>
            </function>
            
            <!-- orig property>fcs/flap-pos-norm</property -->
            <!-- orig value>1.5000</value -->
            <function name="aero/coefficient/dCLflap">
                <description>Delta_Lift_due_to_flaps</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <table>
                      <independentVar>fcs/flap-pos-deg</independentVar>
                      <tableData>
                      00.00	0.000
                      07.23	0.290  <!-- 0.25  0.29008 -->
                      15.46	0.420  <!-- 0.53 0.39467 -->
                      23.64	0.015  <!-- 0.79 0.0133 -->
                      30.00	0.010  <!-- 1.00 0.01 -->
                      </tableData>
                    </table>
                </product>
            </function>
            <function name="aero/coefficient/dCLsb">
                <description>Delta_Lift_due_to_speedbrake</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/speedbrake-pos-norm</property>
                    <value>-0.0830</value>   <!-- -0.08 -->
                </product>
            </function>
            <function name="aero/coefficient/CLde">
                <description>Lift_due_to_Elevator_Deflection</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>fcs/elevator-pos-rad</property>
                    <value>0.2000</value>
                </product>
            </function>
        </axis>

        <axis name="ROLL">
            <function name="aero/coefficient/Clb">
                <description>Roll_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                    <value>-0.1000</value>
                </product>
            </function>
            <function name="aero/coefficient/Clp">
                <description>Roll_moment_due_to_roll_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/p-aero-rad_sec</property>
                    <value>-0.4000</value>
                </product>
            </function>
            <function name="aero/coefficient/Clr">
                <description>Roll_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>0.1500</value>
                </product>
            </function>
            <function name="aero/coefficient/Clda">
                <description>Roll_moment_due_to_aileron</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	0.1000
                              2.0000	0.0330
                          </tableData>
                      </table>
                </product>
            </function>
            <function name="aero/coefficient/Cldr">
                <description>Roll_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>0.0100</value>
                </product>
            </function>
        </axis>

        <axis name="PITCH">
            <function name="aero/coefficient/Cmalpha">
                <description>Pitch_moment_due_to_alpha</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/alpha-rad</property>
                    <value>-0.7000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmde">
                <description>Pitch_moment_due_to_elevator</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>fcs/elevator-pos-rad</property>
                      <table>
                          <independentVar>velocities/mach</independentVar>
                          <tableData>
                              0.0000	-1.3000
                              2.0000	-0.3250
                          </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>-21.0000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cmadot">
                <description>Pitch_moment_due_to_alpha_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/cbarw-ft</property>
                    <property>aero/ci2vel</property>
                    <property>aero/alphadot-rad_sec</property>
                    <value>-4.0000</value>
                </product>
            </function>
        </axis>

        <axis name="YAW">
            <function name="aero/coefficient/Cnb">
                <description>Yaw_moment_due_to_beta</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/beta-rad</property>
                    <value>0.1200</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnr">
                <description>Yaw_moment_due_to_yaw_rate</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>aero/bi2vel</property>
                    <property>velocities/r-aero-rad_sec</property>
                    <value>-0.1500</value>
                </product>
            </function>
            <function name="aero/coefficient/Cndr">
                <description>Yaw_moment_due_to_rudder</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/rudder-pos-rad</property>
                    <value>-0.1000</value>
                </product>
            </function>
            <function name="aero/coefficient/Cnda">
                <description>Adverse_yaw</description>
                <product>
                    <property>aero/qbar-psf</property>
                    <property>metrics/Sw-sqft</property>
                    <property>metrics/bw-ft</property>
                    <property>fcs/left-aileron-pos-rad</property>
                    <value>0.0000</value>
                </product>
            </function>
        </axis>
    </aerodynamics>
    <external_reactions>
 	  <force name="pushback" frame="BODY">
	      <location unit="IN">
		   <x>12.150</x>
		   <y>-0.875</y>
		   <z>1.641</z>
		</location>
	      <direction>
		   <x>-1</x>
		   <y>0</y>
		   <z>0</z>
		</direction>
	 </force>
    </external_reactions>


</fdm_config>
