ERJ175.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="ERJ-170" version="2.0" release="BETA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

<fileheader>
  <author> Narendran Muraleedharan</author>
  <filecreationdate> 2011-08-08 </filecreationdate>el
  <version>$Revision: 1.10 $</version>
  <description> Flight Dynamics Model for the Embraer 170 </description>
</fileheader>

<!-- UNIT CONVERSIONS :
1 meter = 3.2 feet
1 meter = 39.4 inches
1 sq. m = 10.24 sq. ft.
1 feet  = 12 inches -->

<metrics>
<!-- Calculated Wing Area -->
   <wingarea  unit="FT2">616.5924 </wingarea>
<!-- Wingspan = 83.2 ft from wikipeda -->
   <wingspan  unit="FT" >  83.2 </wingspan>
<!-- Wing Incidence = 3 deg from Aeromatic -->
   <wing_incidence unit="DEG"> 3 </wing_incidence>
<!-- Chord = 4.6 m from Ac3D -->
   <chord     unit="FT" >   14.72 </chord>
<!-- Horizontal Tail Area = 18.9735 sq m (calculated on paper) -->
   <htailarea unit="FT2">  194.28864 </htailarea>
<!-- Horizontal Tail Arm = 14.2 m from Ac3D -->
   <htailarm  unit="FT" >   45.44 </htailarm>
<!-- Vertical Tail Area = 17.2975 sq m (calculated on paper) -->
   <vtailarea unit="FT2">  177.1264 </vtailarea>
   <vtailarm  unit="FT" >   0 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
<!-- Center of AircrafT (0,0,0 in Ac3D) is taken as the Eyepoint -->
   <location name="EYEPOINT" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
<!-- Center of Aircraft (in Ac3D) is taken as the Vehicle Reference Point -->
   <location name="VRP" unit="IN">
     <x> 0 </x>
     <y> 0 </y>
     <z> 0 </z>
   </location>
</metrics>

<mass_balance>
<!-- I let the intertia values remain as from Aeromatic as I don't know how to calculate it. It should work out as for this is set to an idea Transonic Aircraft. If I feel that the plane needs to turn slower, or be heavier in that aspect, I can just increase the value to what I need it to be -->
        <ixx unit="SLUG*FT2">    562000 </ixx>
        <iyy unit="SLUG*FT2"> 1.473e+06 </iyy>
        <izz unit="SLUG*FT2">    762000 </izz>
	<ixy unit="SLUG*FT2">         0 </ixy>
	<ixz unit="SLUG*FT2">         0 </ixz>
	<iyz unit="SLUG*FT2">         0 </iyz>
<!-- Operational Empty Weight = 44,600 lbs from wikipedia -->
   <emptywt unit="LBS" > 46600 </emptywt>
<!-- Center of Gravity (Approximate) = (-4.44,0,-0.18) m -->
   <location name="CG" unit="IN">
     <x> -40.936 </x>
     <y>   0.00 </y>
     <z> -7.092 </z>
   </location>

	<pointmass name="Crew">
		<weight unit="LBS">300</weight>
		<location name="POINTMASS" unit="IN">
			<x>-416.458</x>
			<y>0</y>
			<z>1.14</z>
		</location>
	</pointmass>
	<pointmass name="Passengers">
		<weight unit="LBS">13000</weight>
		<location name="POINTMASS" unit="IN">
			<x>-72.102</x>
			<y>0</y>
			<z>1.14</z>
		</location>
	</pointmass>

</mass_balance>

<ground_reactions>

<!-- Nose Gear Contact Point -->
  <contact type="BOGEY" name="NOSE_GEAR">
   <location unit="IN">
     <x> -425.52 </x>
     <y> 0.00 </y>
     <z> -89.832 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
	<spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
	<damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG"> 70 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
</contact>

<!-- Left Main Gear Contact Point -->
  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> -10.43 </x>
     <y> -101.258 </y>
     <z> -93.772 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
	<spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
	<damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
</contact>

<!-- Right Main Gear Contact Point -->
  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="IN">
     <x> -10.43 </x>
     <y> 101.258 </y>
     <z> -93.772 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
	<spring_coeff unit="LBS/FT"> 180000 </spring_coeff>
	<damping_coeff unit="LBS/FT/SEC"> 33957 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
</contact>

<!-- Left Wing Tip Contact Point -->
  <contact type="STRUCTURE" name="LEFT_WING_TIP">
    <location unit="IN">
     <x> 102.44 </x>
     <y> -490.924 </y>
     <z> 10.64 </z>
    </location>
    <static_friction>  0.9 </static_friction>
    <dynamic_friction> 0.8 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

<!-- Right Wing Tip Contact Point -->
  <contact type="STRUCTURE" name="RIGHT_WING_TIP">
    <location unit="IN">
     <x> 102.44 </x>
     <y> 490.924 </y>
     <z> 10.64 </z>
    </location>
    <static_friction>  0.9 </static_friction>
    <dynamic_friction> 0.8 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

<!-- Tail (in case of a tail strike) Contact Point -->
  <contact type="STRUCTURE" name="TAIL_STRIKE">
    <location unit="IN">
     <x> 582.6938 </x>
     <y> 0 </y>
     <z> 45.62914 </z>
    </location>
    <static_friction>  0.95 </static_friction>
    <dynamic_friction> 0.9 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

<!-- Nose (used for Ditching) Contact Point -->
  <contact type="STRUCTURE" name="TAIL_STRIKE">
    <location unit="IN">
     <x> -541.75 </x>
     <y> 0 </y>
     <z> -28.762 </z>
    </location>
    <static_friction>  0.95 </static_friction>
    <dynamic_friction> 0.9 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      200000.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 10000.00 </damping_coeff>
    <brake_group> NONE </brake_group>
    <retractable>0</retractable>
</contact>

</ground_reactions>

<!-- 2 x General Electric CF34-8E Engines -->
<propulsion>

   <engine file="GE_CF34-8E">
    <location unit="IN">
      <x> -157.6 </x>
      <y> -157.6 </y>
      <z> -43.34 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> -157.6 </x>
      <y> -157.6 </y>
      <z> -43.34 </z>
     </location>
     <orient unit="DEG">
       <pitch> -2.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="GE_CF34-8E">
    <location unit="IN">
      <x> -157.6 </x>
      <y> 157.6 </y>
      <z> -43.34 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <feed>2</feed>
    <thruster file="direct">
     <location unit="IN">
      <x> -157.6 </x>
      <y> 157.6 </y>
      <z> -43.34 </z>
     </location>
     <orient unit="DEG">
       <pitch> -2.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- Wing Fuel Tank LEFT -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> 33.096 </x>
       <y> -133.96 </y>
       <z> -5.91 </z>
     </location>
     <capacity unit="KG"> 2500 </capacity>
     <contents unit="KG"> 2000 </contents>
  </tank>

<!-- Central Fuel Tank -->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> -30.072 </x>
       <y> 0.00 </y>
       <z> -36.642 </z>
     </location>
     <capacity unit="KG"> 3000 </capacity>
     <contents unit="KG"> 2800 </contents>
  </tank>

<!-- Wing Fuel Tank RIGHT -->
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 33.096 </x>
       <y> 133.96 </y>
       <z> -5.91 </z>
     </location>
     <capacity unit="KG"> 2500 </capacity>
     <contents unit="KG"> 2000 </contents>
  </tank>

<!-- Trim Fuel Tank -->
  <tank type="FUEL" number="3">
     <location unit="IN">
       <x> 494.864 </x>
       <y> 0 </y>
       <z> 54.372 </z>
     </location>
     <capacity unit="KG"> 800 </capacity>
     <contents unit="KG"> 733 </contents>
  </tank>

</propulsion>

    <system file="pushback"/>

<flight_control name="FCS: ERJ-175">

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

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <range>
        <min> -0.192 </min>
        <max>  0.3310 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <range>
        <min> -0.336 </min>
        <max>  0.3865 </max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>

  </channel>

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

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-trim-sum</input>
      <range>
        <min> -0.45 </min>
        <max>  0.45 </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> -0.45 </min>
        <max>  0.45 </max>
      </range>
      <output>fcs/right-aileron-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="left aileron normalization">
      <input>fcs/left-aileron-pos-rad</input>
      <domain>
        <min> -0.45 </min>
        <max>  0.45 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/left-aileron-pos-norm</output>
   </aerosurface_scale>

   <aerosurface_scale name="right aileron normalization">
      <input>fcs/right-aileron-pos-rad</input>
      <domain>
        <min> -0.45 </min>
        <max>  0.45 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/right-aileron-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <clipto>
        <min> -0.50 </min>
        <max>  0.50 </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>

         <scheduled_gain name="Yaw Damper">
                <input>velocities/r-aero-rad_sec</input>
                <table>
                  <independentVar>velocities/mach</independentVar>
                    <tableData>
                        0.00	0.0
                        0.10	0.0
                        0.11	1.0
                    </tableData>
                </table>
            </scheduled_gain>

            <scheduled_gain name="Yaw Damper Final">
                <input>fcs/yaw-damper</input>
                <table>
                  <independentVar>velocities/mach</independentVar>
                    <tableData>
                        0.00	0.0
                        0.10	0.0
                        0.11	1.0
                    </tableData>
                </table>
            </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-final</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <range>
        <min> -0.530 </min>
        <max>  0.530 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.530 </min>
        <max>  0.530 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/rudder-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Flaps">
   <kinematic name="Flaps Control">
     <input>fcs/flap-cmd-norm</input>
     <traverse>
                <setting>
                    <position>0.0</position>
                    <time>0.0000</time>
                </setting>
                <setting>
                    <position>10.000</position>
                    <time>5.0000</time>
                </setting>
                <setting>
                    <position>25.0000</position>
                    <time>10.0000</time>
                </setting>
                <setting>
                    <position>30.0000</position>
                    <time>10.0000</time>
                </setting>
                <setting>
                    <position>40.0000</position>
                    <time>10.0000</time>
                </setting>
     </traverse>
     <output>fcs/flap-pos-deg</output>
   </kinematic>

   <aerosurface_scale name="flap normalization">
      <input>fcs/flap-pos-deg</input>
      <domain>
        <min>  0 </min>
        <max> 35 </max>
      </domain>
      <range>
        <min> 0 </min>
        <max> 1 </max>
      </range>
      <output>fcs/flap-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Landing Gear">
   <kinematic name="Gear Control">
     <input>gear/gear-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     15 </time>
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>

  </channel>

  <channel name="Speedbrake">
   <kinematic name="Speedbrake Control">
     <input>fcs/speedbrake-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     1 </time>
       </setting>
     </traverse>
     <output>fcs/speedbrake-pos-norm</output>
   </kinematic>

  </channel>

</flight_control>

<aerodynamics>

<!-- Lift due to ground effects to make the take off faster -->
        <function name="aero/function/kCLge">
            <description>Change_in_lift_due_to_ground_effect</description>
            <product>
                  <table>
                      <independentVar>aero/h_b-mac-ft</independentVar>
                      <tableData>
                          0.0000	1.2000	
                          0.1000	1.3200	
                          0.1500	1.3600	
                          0.2000	1.4000	
                          1.1000	1.2000	
                      </tableData>
                  </table>
            </product>
        </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-deg</independentVar>
                          <tableData>
				-40 -1.0000
				-30 -0.9000
				-20 -0.8500
				-15 -0.8000
				-10 -0.7500
				-9  -0.7000
				-8  -0.6700
				-7  -0.6300
				-6  -0.5600
				-5  -0.5000
				-4  -0.4200
				-3  -0.3300
				-2  -0.2200
				-1  -0.1100
				 0   0.0000
				 1   0.2000
				 2   0.3500
				 3   0.5000
				 4   0.6500
				 5   0.9000
				 6   1.0500
				 7   1.1500
				 8   1.2500
				 9   1.3500
				 10  1.4500
				 15  1.5000
				 20  1.4000
				 30  1.3000
				 40  0.9000
                          </tableData>
                      </table>
                </product>
            </function>

    <function name="aero/force/Lift_flap">
       <description>Delta Lift due to flaps</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.05 </value>
       </product>
    </function>

    <function name="aero/force/Lift_speedbrake">
       <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>-0.2</value>
       </product>
    </function>

    <function name="aero/force/Lift_elevator">
       <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>0.45</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/force/Drag_basic">
       <description>Drag at zero lift</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -1.57       1.200
             -0.26    0.018
              0.00    0.012
              0.26    0.020
              1.57       1.200
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_induced">
       <description>Induced drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.025</value>
         </product>
    </function>

    <function name="aero/force/Drag_mach">
       <description>Drag due to mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.79      0.001
                1.10      0.043
                1.80      0.055
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/force/Drag_flap">
       <description>Drag due to flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.01 </value>
         </product>
    </function>

    <function name="aero/force/Drag_gear">
       <description>Drag due to gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.003</value>
         </product>
    </function>

    <function name="aero/force/Drag_speedbrake">
       <description>Drag due to speedbrakes</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/speedbrake-pos-norm</property>
           <value>0.07</value>
         </product>
    </function>

    <function name="aero/force/Drag_beta">
       <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/force/Drag_elevator">
       <description>Drag due to Elevator Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.045</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/force/Side_beta">
       <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/moment/Roll_beta">
       <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/moment/Roll_damp">
       <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>-0.4</value>
       </product>
    </function>

    <function name="aero/moment/Roll_yaw">
       <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>0.15</value>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron">
       <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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.100
              2.0    0.033
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder">
       <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>0.01</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/moment/Pitch_alpha">
       <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/moment/Pitch_elevator">
       <description>Pitch moment due to elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                              0.0000	-1.3000	
                              2.0000	-0.3250	
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_damp">
       <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>-17</value>
       </product>
    </function>

    <function name="aero/moment/Pitch_alphadot">
       <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>-6</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <function name="aero/moment/Yaw_beta">
       <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/moment/Yaw_damp">
       <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>-0.15</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_rudder">
       <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>-0.1</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_aileron">
       <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</value>
       </product>
    </function>

  </axis>

</aerodynamics>

	<external_reactions>
		<force name="pushback" frame="BODY">
			<location unit="IN">
				<x>294</x>
				<y>0</y>
				<z>-149</z>
			</location>
			<direction>
				<x>1</x>
				<y>0</y>
				<z>0</z>
			</direction>
		</force>
	</external_reactions>
</fdm_config>