<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="MRJ90-STD" version="2.0" release="ALPHA"
	    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
	    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

  <fileheader>
    <author> Tatsuhiro Nishioka </author>
    <filecreationdate> 2009-07-29 </filecreationdate>
    <version>$Revision$</version>
    <description> MRJ (JSBSim) </description>
  </fileheader>

  <!--
      File:     MRJ90-STD.xml
      Inputs:
      name:          MRJ90-STD - Mitsubishi Regional Jet
      type:          two-engine transonic transport
      max weight:    87300 lb
      wing span:     97.6 ft
      length:        118.0 ft
      wing area:     773.50 sq-ft
      gear type:     tricycle
      retractable?:  yes
      # engines:     2
      engine type:   turbine
      engine layout: wings
      yaw damper?    yes
      Outputs:
      wing loading:  105.60 lb/sq-ft
      CL-alpha:      4.4 per radian
      CL-0:          0.2
      CL-max:        1.2
      CD-0:          0.02
      K:             0.043

    -->

  <metrics>
    <wingarea  unit="FT2">  773.50 </wingarea>
    <wingspan  unit="FT" >   97.60 </wingspan>
    <wing_incidence>          2.00 </wing_incidence>
    <chord     unit="FT" >    9.55 </chord>
    <htailarea unit="FT2">  214.38 </htailarea>
    <htailarm  unit="FT" >   58.66 </htailarm>
    <vtailarea unit="FT2">  172.00 </vtailarea>
    <vtailarm  unit="FT" >   54.85 </vtailarm>
    <location name="AERORP" unit="M">
      <x>  -0.39 </x>
      <y>   0.00 </y>
      <z>   0.00 </z>
    </location>
    <location name="EYEPOINT" unit="M">
      <x> -15.28 </x>
      <y>  -0.55 </y>
      <z>   1.18 </z>
    </location>
    <location name="VRP" unit="M">
      <x>0</x>
      <y>0</y>
      <z>0</z>
    </location>
  </metrics>

  <mass_balance>
    <ixx unit="SLUG*FT2">    242119 </ixx>
    <iyy unit="SLUG*FT2">    817675 </iyy>
    <izz unit="SLUG*FT2">   1000006 </izz>
    <emptywt unit="LBS" >     54895 </emptywt> <!-- 25,000 kg -->
    <location name="CG" unit="M">
      <x> -1.04 </x>
      <y>  0.00 </y>
      <z>  0.00 </z>
    </location>

    <pointmass name="Pilot">
      <weight unit="LBS"> 150 </weight> <!-- 68 kg -->
      <location name="POINTMASS" unit="M">
	<x> -15.20 </x>
	<y> -0.50 </y>
	<z>  0.15</z>
      </location>
    </pointmass>

    <pointmass name="Co-pilot">
      <weight unit="LBS"> 150 </weight> <!-- 68 kg -->
      <location name="POINTMASS" unit="M">
	<x> -15.20 </x>
	<y>  0.50 </y>
	<z>  0.15</z>
      </location>
    </pointmass>

    <pointmass name="Passengers and Baggages">
      <weight unit="LBS"> 12264 </weight> <!-- 5,600 kg -->
      <location name="POINTMASS" unit="M">
	<x> -1.14 </x>
	<y>  0.00 </y>
	<z>  0.15</z>
      </location>
    </pointmass>
  </mass_balance>

  <ground_reactions>

    <contact type="BOGEY" name="NOSE">
      <location unit="M">
	<x> -15.17 </x>
	<y>   0.00 </y>
	<z>  -2.35 </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">      26190.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC">  8730.00 </damping_coeff>
      <max_steer unit="DEG"> 5.00 </max_steer>
      <brake_group>NONE</brake_group>
      <retractable>1</retractable>
    </contact>

    <contact type="BOGEY" name="LEFT_MAIN">
      <location unit="M">
	<x>   0.00 </x>
	<y>  -2.57 </y>
	<z>  -2.35 </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">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </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="M">
	<x>   0.00 </x>
	<y>   2.57 </y>
	<z>  -2.35 </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">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
      <max_steer unit="DEG">0</max_steer>
      <brake_group>RIGHT</brake_group>
      <retractable>1</retractable>
    </contact>

    <contact type="STRUCTURE" name="LEFT_WING">
      <location unit="M">
	<x>   4.67 </x>
	<y> -15.65 </y>
	<z>   2.25 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="RIGHT_WING">
      <location unit="M">
	<x>   4.67 </x>
	<y> -15.65 </y>
	<z>   2.25 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="NOSE">
      <location unit="M">
	<x> -18.24 </x>
	<y>   0.00 </y>
	<z>   0.00 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="MID_TAIL_BOTTOM">
      <location unit="M">
	<x> 11.56 </x>
	<y>  0.00 </y>
	<z> -0.05  </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="TAIL">
      <location unit="M">
	<x> 18.81 </x>
	<y>  0.00 </y>
	<z>  1.87 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="LEFT_HSTAB">
      <location unit="M">
	<x> 18.82 </x>
	<y> -5.84 </y>
	<z>  2.34 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="RIGHT_HSTAB">
      <location unit="M">
	<x> 18.82 </x>
	<y>  5.84 </y>
	<z>  2.34 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

    <contact type="STRUCTURE" name="VSTAB">
      <location unit="M">
	<x> 17.18 </x>
	<y>  0.00 </y>
	<z>  7.74 </z>
      </location>
      <static_friction>  0.80 </static_friction>
      <dynamic_friction> 0.50 </dynamic_friction>
      <spring_coeff unit="LBS/FT">      87300.00 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 17460.00 </damping_coeff>
    </contact>

  </ground_reactions>

  <propulsion>

    <engine file="PW1000G-17K">
      <location unit="M">
	<x> -4.00 </x>
	<y> -4.96 </y>
	<z> -0.78 </z>
      </location>
      <orient unit="DEG">
	<pitch> 0.00 </pitch>
	<roll>  0.00 </roll>
	<yaw>   0.00 </yaw>
      </orient>
      <feed>0</feed>
      <feed>1</feed>
      <thruster file="direct">
	<location unit="M">
	  <x> -2.54 </x>
	  <y> -4.96 </y>
	  <z> -0.78 </z>
	</location>
	<orient unit="DEG">
	  <pitch> 0.00 </pitch>
	  <roll>  0.00 </roll>
	  <yaw>   0.00 </yaw>
	</orient>
      </thruster>
    </engine>

    <engine file="PW1000G-17K">
      <location unit="M">
	<x> -4.00 </x>
	<y>  4.96 </y>
	<z> -0.78 </z>
      </location>
      <orient unit="DEG">
	<pitch> 0.00 </pitch>
	<roll>  0.00 </roll>
	<yaw>   0.00 </yaw>
      </orient>
      <feed>0</feed>
      <feed>1</feed>
      <thruster file="direct">
	<location unit="M">
	  <x> -2.54 </x>
	  <y>  4.96 </y>
	  <z> -0.78 </z>
	</location>
	<orient unit="DEG">
	  <pitch> 0.00 </pitch>
	  <roll>  0.00 </roll>
	  <yaw>   0.00 </yaw>
	</orient>
      </thruster>
    </engine>

    <tank type="FUEL" number="0">
      <location unit="M">
	<x> -1.22 </x>
	<y> -2.49 </y>
	<z>  0.00 </z>
      </location>
      <capacity unit="LBS"> 9920.8  </capacity>
      <contents unit="LBS"> 7920.8 </contents>
    </tank>

    <tank type="FUEL" number="1">
      <location unit="M">
	<x> -1.22 </x>
	<y>  2.49 </y>
	<z>  0.00 </z>
      </location>
      <capacity unit="LBS"> 9920.8 </capacity>
      <contents unit="LBS"> 7920.8 </contents>
    </tank>

  </propulsion>

  <flight_control name="FCS: MRJ">

    <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>

<!--
      <scheduled_gain name="Pitch Scheduled Gain 1"> 
        <input>fcs/pitch-gain-1</input> 
        <gain>0.017</gain> 
        <table> 
          <independentVar>fcs/elevator-pos-rad</independentVar> 
          <tableData> 
            -0.68  -26.548 
            -0.595 -20.513 
            -0.51  -15.328 
             … 
             0.527 -20.513 
             0.612 -26.548 
             0.697 -33.433 
          </tableData> 
        </table> 
      </scheduled_gain> 
-->

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

      <aerosurface_scale name="elevator normalization">
	<input>fcs/elevator-pos-rad</input>
	<domain>
          <min> -0.35 </min>
          <max>  0.35 </max>
	</domain>
	<range>
          <min> -1 </min>
          <max>  1 </max>
	</range>
	<output>fcs/elevator-pos-norm</output>
      </aerosurface_scale>

    </channel>

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

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

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

      <aerosurface_scale name="left aileron normalization">
	<input>fcs/left-aileron-pos-rad</input>
	<domain>
          <min> -0.35 </min>
          <max>  0.35 </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> -0.35 </min>
          <max>  0.35 </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> -0.35 </min>
          <max>  0.35 </max>
	</clipto>
      </summer>

      <scheduled_gain name="Yaw Damper Rate">
	<input>velocities/r-aero-rad_sec</input>
	<table>
          <independentVar lookup="row">velocities/ve-kts</independentVar>
          <tableData>
            30     0.00
            60     2.00
          </tableData>
	</table>
      </scheduled_gain>

      <scheduled_gain name="Yaw Damper Beta">
	<input>aero/beta-rad</input>
	<table>
          <independentVar lookup="row">velocities/ve-kts</independentVar>
          <tableData>
            30     0.00
            60     0.00
          </tableData>
	</table>
      </scheduled_gain>

      <summer name="Yaw Damper Sum">
	<input>fcs/yaw-damper-beta</input>
	<input>fcs/yaw-damper-rate</input>
	<clipto>
          <min> -0.1 </min>
          <max>  0.1 </max>
	</clipto>
      </summer>

      <scheduled_gain name="Yaw Damper Final">
	<input>fcs/yaw-damper-sum</input>
	<table>
          <independentVar lookup="row">velocities/ve-kts</independentVar>
          <tableData>
            30         0.0
            31         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> -0.35 </min>
          <max>  0.35 </max>
	</range>
	<output>fcs/rudder-pos-rad</output>
      </aerosurface_scale>

      <aerosurface_scale name="rudder normalization">
	<input>fcs/rudder-pos-rad</input>
	<domain>
          <min> -0.35 </min>
          <max>  0.35 </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 </position>
            <time>      0 </time>
	  </setting>
	  <setting>
            <position> 15 </position>
            <time>      4 </time>
	  </setting>
	  <setting>
            <position> 30 </position>
            <time>      3 </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> 30 </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>     5 </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>

    <axis name="LIFT">

      <function name="aero/coefficient/CLalpha">
	<description>Lift_due_to_alpha</description>
	<product>
          <property>aero/qbar-psf</property> <!-- dynamic pressure 0-600 f(velocity) -->
          <property>metrics/Sw-sqft</property> <!-- = wing area -->
          <property>aero/ACLalpha-coeff</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -0.20 -0.680
              0.00  0.300  <!--  0 deg -->
              0.09  0.900  <!--  5 deg -->
              0.17  1.850  <!-- 10 deg -->
              0.26  2.350  <!-- 15 deg -->
              0.35  2.760  <!-- 20 deg -->
              0.42  2.840  <!-- 24 deg -->
              0.44  2.280  <!-- 25 deg -->
              0.60  0.600
            </tableData>
          </table>
	</product>
      </function>

      <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        1.2030
              0.1000        1.1270
              0.1500        1.0900
              0.2000        1.0730
              0.3000        1.0460
              0.4000        1.0550
              0.5000        1.0190
              0.6000        1.0130
              0.7000        1.0080
              0.8000        1.0060
              0.9000        1.0030
              1.0000        1.0020
              1.1000        1.0000
            </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> <!-- = wing area -->
          <property>fcs/flap-pos-deg</property>
          <property>aero/function/kCLge</property>
          <property>aero/ACLflap-coeff</property>
          <value> 0.05900 </value>
	</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/CLde">
	<description>Lift_due_to_Elevator_Deflection</description>
	<product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property> <!-- = wing area -->
          <property>fcs/elevator-pos-rad</property>
          <property>aero/Aelevator-deflection-coeff</property>
          <value>0.20</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>aero/ACD0-coeff</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -1.57       1.500
              -0.26    0.026
	      0.00   0.038
              0.09   0.045
              0.17   0.055
              0.26   0.068
              0.35   0.093
              0.38   0.104
              0.40   0.113
              0.42   0.124
              0.44   0.140
              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/cl-squared</property>
          <value>0.043</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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.00      0.000
              0.79      0.000
              0.90      0.019
              1.10      0.023
              1.80      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>
          <property>fcs/flap-pos-deg</property>
          <property>aero/ACDflap-coeff</property>
          <value> 0.0076 </value>
        </product>
      </function>

      <function name="aero/coefficient/CDgear">
	<description>Drag_due_to_gear</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>gear/gear-pos-norm</property>
          <value>0.015</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/elevator-pos-norm</property></abs>
          <value>0.04</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>-0.4</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>0.15</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 lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.100
              2.0    0.033
            </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>0.01</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/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.500
              0.4     -0.900
              0.7     -0.700     
              2.0     -0.100
            </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>-17</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>-6</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>0.12</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>-0.15</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>-0.1</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</value>
	</product>
      </function>

    </axis>

  </aerodynamics>

</fdm_config>
