KC-137R.xml

<?xml version="1.0"?>
<!--###################################################################################
		Lake of Constance Hangar :: M.Kraus
		Boeing 707 for Flightgear Septemper 2013
		This file is licenced under the terms of the GNU General Public Licence V2 or later
		###################################################################################
-->
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="707" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author>M.Kraus :: Lake of Constance Hangar</author>
  <filecreationdate>2014-02-24</filecreationdate>
  <version>2.2.4</version>
  <description>Boeing 707 CFM-56</description>
 </fileheader>

<!--
  File:     707.xml
  Inputs:
    name:          707
    type:          four-engine transonic transport
    max weight:    333795.105 lb
    wing span:     142.3954 ft
    length:        152.92741 ft
    wing area:     3046.483963 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   turbine
    engine layout: wings
    yaw damper:    smooth yoke behaviour
  Outputs:
    wing loading:  109.57 lb/sq-ft
    payload:       45108.5 lbs
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.2
    CD-0:          0.017
    K:             0.042
 -->

	<metrics>
   <wingarea  unit="FT2"> 3046.48 </wingarea>
   <wingspan  unit="FT" >  142.40 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   21.39 </chord>
   <htailarea unit="FT2">  761.62 </htailarea>
   <htailarm  unit="FT" >   68.82 </htailarm>
   <vtailarea unit="FT2">  609.30 </vtailarea>
   <vtailarm  unit="FT" >   68.82 </vtailarm>

		<location name="AERORP" unit="IN">
			<x>  0.00 </x>
			<y>  0.00 </y>
			<z>  0.00 </z>
		</location>
		<location name="EYEPOINT" unit="IN">
			<x>  0.00 </x>
			<y>  0.00 </y>
			<z>  0.00 </z>
		</location>
		<location name="VRP" unit="IN">
			<x>  0.00</x>
			<y>  0.00</y>
			<z>  0.00</z>
		</location>
	</metrics>

	<mass_balance>
		 <ixx unit="SLUG*FT2">   2322405 </ixx>
		 <iyy unit="SLUG*FT2">   2886669 </iyy>
		 <izz unit="SLUG*FT2">   5260000 </izz>
		 <emptywt unit="LBS" >    137526 </emptywt>
		<location name="CG" unit="IN">
			<x>  0.0 </x>
			<y>  0.0 </y>
			<z>-45.20 </z>
		</location>
		<pointmass name="CREW">
			  <weight unit="LBS">540</weight>
			  <location name="POINTMASS" unit="IN">
			  <x>-600</x>
			  <y>   0</y>
			  <z>   0</z>
			  </location>
		</pointmass>
		<pointmass name="PASSENGER FIRST CLASS">
			  <weight unit="LBS"> 0</weight><!-- passengers-->
			  <location name="POINTMASS" unit="IN">
			  <x>-400</x>
			  <y>  0</y>
			  <z>  0</z>
			  </location>
		</pointmass>
		<pointmass name="PASSENGER SECOND CLASS">
			  <weight unit="LBS"> 0</weight><!-- passengers-->
			  <location name="POINTMASS" unit="IN">
			  <x>-100</x>
			  <y>   0</y>
			  <z>   0</z>
			  </location>
		</pointmass>
		<pointmass name="PASSENGER SECOND CLASS">
			  <weight unit="LBS"> 0</weight><!-- passengers-->
			  <location name="POINTMASS" unit="IN">
			  <x>  50</x>
			  <y>   0</y>
			  <z>   0</z>
			  </location>
		</pointmass>
		<pointmass name="LUGGAGE 1">
			  <weight unit="LBS">  0</weight><!-- cargo or more passengers -->
			  <location name="POINTMASS" unit="IN">
			  <x>-400</x>
			  <y>   0</y>
			  <z>   0</z>
			  </location>
		</pointmass>
		<pointmass name="LUGGAGE 2">
			  <weight unit="LBS">  0</weight><!-- cargo or more passengers -->
			  <location name="POINTMASS" unit="IN">
			  <x>-100</x>
			  <y>   0</y>
			  <z>   0</z>
			  </location>
		</pointmass>
		<pointmass name="LUGGAGE 3">
			  <weight unit="LBS">  0</weight><!-- cargo or more passengers -->
			  <location name="POINTMASS" unit="IN">
			  <x> 50</x>
			  <y>  0</y>
			  <z>  0</z>
			  </location>
		</pointmass>
	</mass_balance>
	
 <ground_reactions>
 
  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> -618.44 </x>
     <y>   0.00 </y>
     <z> -114.00 </z>
   </location>
    <static_friction>  0.55 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <rolling_friction> 0.02 </rolling_friction>
    <spring_coeff unit="LBS/FT"> 90000 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 6000 </damping_coeff>
    <damping_coeff_rebound unit="LBS/FT/SEC">12000</damping_coeff_rebound>
    <relaxation_velocity>
      <rolling unit="FT/SEC">0.6</rolling>
      <side unit="FT/SEC">0.6</side>
    </relaxation_velocity>
    <force_lag_filter>
      <rolling> 120.0 </rolling>
      <side>120.0 </side>
    </force_lag_filter>
    <wheel_slip_filter> 120.0 </wheel_slip_filter>
    <max_steer unit="DEG"> 35 </max_steer>
    <brake_group> NONE </brake_group>
    <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x>  71.65 </x>
     <y> -98.81 </y>
     <z> -116.3 </z>
   </location>
   <static_friction>  0.55 </static_friction>
   <dynamic_friction> 0.70 </dynamic_friction>
   <rolling_friction> 0.04 </rolling_friction>
   <spring_coeff unit="LBS/FT">     230000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">140000.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x> 71.65 </x>
     <y> 98.81 </y>
     <z> -116.3 </z>
   </location>
   <static_friction>  0.55 </static_friction>
   <dynamic_friction> 0.70 </dynamic_friction>
   <rolling_friction> 0.04 </rolling_friction>
   <spring_coeff unit="LBS/FT">     230000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">140000.00 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>
 
  <contact type="STRUCTURE" name="NOSE_CRASHED">
    <location unit="IN">
     <x> -618.44 </x>
     <y>   0.00 </y>
     <z> -50.00 </z>
    </location>
    <static_friction>  0.55 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      360600.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 80000.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="IN">
     <x> 411.00 </x>
     <y> -72.88 </y>
     <z> -43.65 </z>
    </location>
    <static_friction>  0.55 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      360600.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 80000.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 411.00 </x>
     <y>  72.88 </y>
     <z> -43.65 </z>
    </location>
    <static_friction>  0.55 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
   <spring_coeff unit="LBS/FT">      360600.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 80000.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="cfm56_1">
    <location unit="IN">
      <x>  22.11 </x>
      <y>-293.50 </y>
      <z> -46.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
	<feed>3</feed>
    <feed>5</feed>
    <feed>6</feed>
    <thruster file="direct">
     <location unit="IN">
      <x>  22.11 </x>
      <y>-293.50 </y>
      <z> -46.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="cfm56_2">
    <location unit="IN">
      <x>-164.20 </x>
      <y>-197.62 </y>
      <z> -77.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
	<feed>3</feed>
    <feed>4</feed>
    <feed>6</feed>
    <thruster file="direct">
     <location unit="IN">
      <x>-164.20 </x>
      <y>-197.62 </y>
      <z> -77.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="cfm56_3">
    <location unit="IN">
      <x>-164.20 </x>
      <y> 197.62 </y>
      <z> -77.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
	<feed>3</feed>
    <feed>2</feed>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN">
      <x>-164.20 </x>
      <y> 197.62 </y>
      <z> -77.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="cfm56_4">
    <location unit="IN">
      <x>  22.11 </x>
      <y> 293.50 </y>
      <z> -46.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
	<feed>3</feed>
    <feed>1</feed>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN">
      <x>  22.11 </x>
      <y> 293.50 </y>
      <z> -46.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>
  
  <!-- Reserve 4 tank right -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x>   39.37 </x>
       <y>  700.00 </y>
       <z>  -16.65 </z>
     </location>
     <capacity unit="LBS"> 2941.00 </capacity>
     <contents unit="LBS"> 1470.00 </contents>
	 <priority>2</priority>
  </tank>
  <!-- Main 4 tank right -->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x>  120.12 </x>
       <y>  507.10 </y>
       <z>  -16.65 </z>
     </location>
     <capacity unit="LBS"> 15564.00 </capacity>
     <contents unit="LBS">  7782.00 </contents>
	 <priority>1</priority>
  </tank>
  <!-- Main 3 tank right -->
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x>  -74.10 </x>
       <y>  176.30 </y>
       <z>  -16.65 </z>
     </location>
     <capacity unit="LBS"> 27262.00 </capacity>
     <contents unit="LBS"> 13631.00 </contents>
	 <priority>1</priority>
  </tank>
  <!-- center tank -->
  <tank type="FUEL" number="3">
     <location unit="IN">
       <x>   0.0 </x>
       <y>   0.0 </y>
       <z> -16.65 </z>
     </location>
     <capacity unit="LBS"> 68293.00 </capacity>
     <contents unit="LBS"> 34146.00 </contents>
	 <priority>0</priority>
  </tank>
  <!-- Main 2 tank left -->
  <tank type="FUEL" number="4">
     <location unit="IN">
       <x>  -74.10 </x>
       <y> -176.30 </y>
       <z>  -16.65 </z>
     </location>
     <capacity unit="LBS"> 27262.00 </capacity>
     <contents unit="LBS"> 13631.00 </contents>
	 <priority>1</priority>
  </tank>
  <!-- Main 1 tank left --> 
  <tank type="FUEL" number="5">
     <location unit="IN">
       <x>  120.12 </x>
       <y> -507.10 </y>
       <z>  -16.65 </z>
     </location>
     <capacity unit="LBS"> 15564.00 </capacity>
     <contents unit="LBS">  7782.00 </contents>
	 <priority>1</priority>
  </tank>  
  <!-- Reserve 1 tank left -->
  <tank type="FUEL" number="6">
     <location unit="IN">
       <x>   39.37 </x>
       <y> -700.00 </y>
       <z>  -16.65 </z>
     </location>
     <capacity unit="LBS"> 2941.00 </capacity>
     <contents unit="LBS"> 1470.00 </contents>
	 <priority>2</priority>
  </tank>

 </propulsion> 
 
 <system file="pushback"/>
 <system file="libraries-jsb"/>
 <system file="fbw"/>
 <system file="fcs"/>
 <system file="cfm56"/>
 <system file="glass-effect"/>

 <flight_control name="none"/>

 <aerodynamics>

	<function name="aero/function/kCLge">
		<description>Lift factor due to ground effect</description>
		<table>
			<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
			<tableData>
				0.00  1.203
				0.10  1.127
				0.15  1.090
				0.20  1.073
				0.30  1.046
				0.40  1.055
				0.50  1.019
				0.60  1.013
				0.70  1.008
				0.80  1.006
				0.90  1.003
				1.00  1.002
				1.10  1.000
			</tableData>
		</table>
	</function>
	
	<function name="aero/function/kCDge">
		<description>Drag factor due to ground effect</description>
		<table>
			<independentVar lookup="row">aero/h_b-mac-ft</independentVar>
			<tableData>
				0.00  0.480
				0.10  0.515
				0.15  0.629
				0.20  0.709
				0.30  0.815
				0.40  0.882
				0.50  0.928
				0.60  0.962
				0.70  0.988
				0.80  1.000
			</tableData>
		</table>
	</function>

  <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>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -0.20   -0.780
               0.00    0.170
               0.23    1.400
               0.50    0.740
               0.60    0.340
               
               <!--
              -0.20   -0.680
               0.00    0.240
               0.23    1.400
               0.60    0.740
               -->
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/coefficient/dCLflap">
        <description>Delta_Lift_due_to_flaps</description>
        <product>
            <property>aero/qbar-psf</property>
            <property>metrics/Sw-sqft</property>
            <property>aero/function/kCLge</property>
              <table>
                  <independentVar>fcs/flap-pos-deg</independentVar>
                  <tableData>
                      0.0000	0.000	
                      2.0000	0.040	
                      4.0000	0.150	
                      6.0000	0.200	
                     10.0000	0.400	
                  </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>-0.1</value>
       </product>
    </function>
   
    <function name="aero/coefficient/CDLEflap">
       <description>Lift_due_to_leading_edge_flaps</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/function/kCLge</property>
           <property>fcs/wing-fold-pos-norm</property>
           <value>0.2</value>
       </product>
    </function>

    <function name="aero/coefficient/CLde">
       <description>Lift_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/pitch-pos-rad</property>
           <value>0.1</value>
       </product>
    </function>
	
    <function name="aero/coefficient/CLdet">
       <description>Lift_due_to_Elevator_Trim_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/pitch-trim-pos-rad</property>
           <value>0.1</value>
       </product>
    </function>
  
  	<function name="aero/coefficient/StabTrim">
       <description>Lift_due_to_stabilizer</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
 		   <property>/b707/stabilizer/cutout</property> <!-- stabilization nose up down with different weights -->
           <value>0.2</value>
       </product>
    </function>

  </axis>

  <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>
	  			<property>/b707/anti-ice/drag-coefficient</property> <!-- if ice is on wings -->
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -1.57    1.500
             -0.26    0.024
              0.00    0.019
              0.26    0.024
              1.57    1.500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/CDi">
       <description>Induced_drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/function/kCDge</property>
           <property>aero/cl-squared</property>
           <property>/b707/anti-ice/drag-coefficient</property> <!-- if ice is on wings -->
           <value>0.044</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>
          <property>/b707/anti-ice/drag-coefficient</property> <!-- if ice is on wings -->
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.0  0.000
                0.9  0.000
                1.1  0.023
                1.8  0.015
            </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>
           <!--<value> 0.018 </value>-->
            <table>
                <independentVar>fcs/flap-pos-deg</independentVar>
                <tableData>
                    0.0000	0.000	
                    2.0000	0.012	
                    4.0000	0.014	<!-- takeoff-->
                    6.0000	0.024	<!-- approach-->
                   10.0000	0.035	<!-- landing -->
                </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>0.011</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>0.02</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 lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57       1.230
              -0.26       0.050
               0.00       0.000
               0.26       0.050
               1.57       1.230
            </tableData>
          </table>
       </product>
    </function>
	
	<function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
         <abs>
           <property>fcs/pitch-pos-norm</property>
         </abs>
           <value>0.02</value>
       </product>
    </function>
	
	<function name="aero/coefficient/CDdet">
       <description>Drag_due_to_Elevator_Trim_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
         <abs>
           <property>fcs/pitch-trim-pos-norm</property>
         </abs>
           <value>0.02</value>
       </product>
    </function>
    
    <function name="aero/coefficient/CDcrash">
       <description>After_crash_drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
	  			 <property>/b707/crashed</property> <!-- if airplane crashed -->
           <value>10</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</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>-0.1</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>-0.65</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>0.005</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/roll-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.150
              2.0    0.053
            </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/yaw-pos-rad</property>
           <value>0.008</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>-0.6</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/pitch-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.073
              2.0     -0.214
            </tableData>
          </table>
       </product>
    </function>
	
    <function name="aero/coefficient/Cmdet">
       <description>Pitch_moment_due_to_elevator_trim</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/pitch-trim-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -0.973
              2.0     -0.184
            </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>-28</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>-1.41</value>
       </product>
    </function>
    
    <function name="aero/coefficient/Cmde_inboard">
        <description>Pitch_moment_due_to_inboard_spoiler</description>
        <product>
            <property>aero/qbar-psf</property>
            <property>metrics/Sw-sqft</property>
            <property>metrics/cbarw-ft</property>
            <property>/b707/trim/spoiler-nose-down</property>
            <table>
                <independentVar>velocities/mach</independentVar>
                <tableData>
                  0.0000    -0.06
                  0.6000    -0.02 
                </tableData>
            </table>
        </product>
    </function>
    <function name="aero/coefficient/Cmde_outboard">
        <description>Pitch_moment_due_to_outboard_spoiler</description>
        <product>
            <property>aero/qbar-psf</property>
            <property>metrics/Sw-sqft</property>
            <property>metrics/cbarw-ft</property>
            <property>/b707/trim/spoiler-nose-up</property>
            <table>
                <independentVar>velocities/mach</independentVar>
                <tableData>
                  0.0000    0.06
                  0.6000    0.02
                </tableData>
            </table>
        </product>
    </function>

  </axis>

  <axis name="YAW"> <!-- ########################################################### -->

    <function name="aero/coefficient/Cnb">
       <description>Yaw_moment_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>0.12</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>-0.11</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/yaw-pos-rad</property>
           <value>0.045</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/roll-pos-rad</property>
           <value>0</value>
       </product>
    </function>

  </axis>
  
 </aerodynamics>
 
 <external_reactions>
	 <force name="pushback" frame="BODY">
		<location unit="IN">
		 <x>  -139 </x>
		 <y>    0.0 </y>
		 <z>  -71.0 </z>
		</location>
		<direction>
		 <x>1</x>
		 <y>0</y>
		 <z>0</z>
		</direction>
	 </force>
 </external_reactions>
 
 <system name="crash-detect">
		<channel name="impact-ground">
		   <switch name="impact">
		   		<test logic="AND" value="1">
		              velocities/mach gt 0.2
		              position/h-agl-ft lt 6.0 
		              position/h-agl-ft gt 0.1   <!-- between EHAM and England there is h-agl-ft to 0 -->
		              simulation/sim-time-sec gt 1.0
		        </test>
		   		<test logic="AND" value="1">
		              position/h-agl-ft lt 5.0
		              position/h-agl-ft gt 0.1   <!-- between EHAM and England there is h-agl-ft to 0 -->
		              simulation/sim-time-sec gt 1.0
		        </test>
		   		<test logic="AND" value="1">
		              position/h-agl-ft lt 5.95
		              position/h-agl-ft gt 0.1   <!-- between EHAM and England there is h-agl-ft to 0 -->
		              /b707/over-water != 0
		              simulation/sim-time-sec gt 1.0
		        </test>
		        <output>systems/crash-detect/crash-on-ground</output>
		   </switch>

		</channel>
	</system>

</fdm_config>