<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="T-50" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Ummon Karpe, Petar Jedvaj </author>
  <filecreationdate> 2012-08-18 </filecreationdate>
  <version>$Revision: 2.0 $</version>
  <description> Sukhoi T-50 PAK FA </description>
 </fileheader>

<!--

  File:     T-50.xml
  Inputs:
    name:          T-50
    type:          two-engine transonic/supersonic fighter
    max weight:    81585 lb
    wing span:     45.934 ft
    length:        64.9638 ft
    wing area:     848.282 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  96.18 lb/sq-ft
    CL-alpha:      3.6 per radian
    CL-0:          0.08
    CL-max:        1
    CD-0:          0.024
    K:             0.12
    
  Manual calculations:
    AR:            2.5
    e:             0.85
    p:             1.25
    Lift-slope:    3.06
    Induced drag:  1.6
    Clmax:         1.5

-->

 <metrics>
   <wingarea  unit="FT2">  900.00 </wingarea>
   <wingspan  unit="FT" >   45.93 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   18.47 </chord>
   <htailarea unit="FT2">  169.66 </htailarea>
   <htailarm  unit="FT" >   25.99 </htailarm>
   <vtailarea unit="FT2">  152.69 </vtailarea>
   <vtailarm  unit="FT" >   25.99 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 467.74 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 155.91 </x>
     <y>   0.00 </y>
     <z>  38.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">     67439 </ixx>
   <iyy unit="SLUG*FT2">    185416 </iyy>
   <izz unit="SLUG*FT2">    196426 </izz>
   <emptywt unit="LBS" >     40000 </emptywt>
   <location name="CG" unit="IN">
     <x> 467.74 </x>
     <y>   0.00 </y>
     <z> -19.49 </z>
   </location>
    <pointmass name="station1">
      <weight unit="LBS"> 440 </weight>
      <location name="POINTMASS" unit="IN">
          <x> 413 </x>
          <y> -11 </y>
          <z>  -7 </z>
      </location>
   </pointmass>
    <pointmass name="station2">
      <weight unit="LBS"> 440 </weight>
      <location name="POINTMASS" unit="IN">
          <x> 413 </x>
          <y>  11 </y>
          <z>  -7 </z>
      </location>
   </pointmass>
   <pointmass name="station3">
      <weight unit="LBS"> 440 </weight>
      <location name="POINTMASS" unit="IN">
          <x> 641 </x>
          <y> -11 </y>
          <z>  -7 </z>
      </location>
   </pointmass>
   <pointmass name="station4">
      <weight unit="LBS"> 440 </weight>
      <location name="POINTMASS" unit="IN">
          <x> 641 </x>
          <y>  11 </y>
          <z>  -7 </z>
      </location>
   </pointmass>
       <pointmass name="station5">
      <weight unit="LBS"> 230 </weight>
      <location name="POINTMASS" unit="IN">
          <x> 413 </x>
          <y>-106 </y>
          <z> -15 </z>
      </location>
   </pointmass>
   <pointmass name="station6">
      <weight unit="LBS"> 230 </weight>
      <location name="POINTMASS" unit="IN">
          <x> 413 </x>
          <y> 106 </y>
          <z> -15 </z>
      </location>
    </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 101.34 </x>
     <y>   0.00 </y>
     <z> -93.55 </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">      24475.50 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  8158.50 </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="IN">
     <x> 486.45 </x>
     <y> -49.61 </y>
     <z> -93.55 </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">      81585.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 16317.00 </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> 486.45 </x>
     <y>  49.61 </y>
     <z> -93.55 </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">      81585.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 16317.00 </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="IN">
     <x> 467.74 </x>
     <y> -22.97 </y>
     <z> -19.49 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      81585.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 16317.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 467.74 </x>
     <y>  22.97 </y>
     <z> -19.49 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      81585.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 16317.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="Saturn">
    <location unit="IN">
      <x> 719.57 </x>
      <y> -20.00 </y>
      <z>   0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 719.57 </x>
       <y> -20.00 </y>
       <z>   0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="Saturn">
    <location unit="IN">
      <x> 719.57 </x>
      <y>  20.00 </y>
      <z>   0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>1</feed>
    <thruster file="direct">
     <location unit="IN">
       <x> 719.57 </x>
       <y>  20.00 </y>
       <z>   0.00 </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="IN">
       <x> 467.74 </x>
       <y>   0.00 </y>
       <z> -19.49 </z>
     </location>
     <capacity unit="LBS"> 11500.00 </capacity>
     <contents unit="LBS"> 5000.00 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 467.74 </x>
       <y>   0.00 </y>
       <z> -19.49 </z>
     </location>
     <capacity unit="LBS"> 11500.00 </capacity>
     <contents unit="LBS"> 5000.00 </contents>
  </tank>

 </propulsion>
 
 <system file="Speedbrakes"/>
 <system file="Chute"/>
 <system file="Armament"/>
 <system file="Canopy"/>
 <system file="Particles"/>

 <flight_control name="FCS: T-50">

  <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>
   
   <pure_gain name="Target Pitch Rate">
      <input>fcs/pitch-trim-sum</input>
      <gain>-60</gain>
   </pure_gain>
   
   <pure_gain name="Pitch Rate">
      <input>velocities/q-rad_sec</input>
      <gain>-57.3</gain>
   </pure_gain>
   
   <summer name="Pitch Rate Error">
      <input>fcs/target-pitch-rate</input>
      <input>fcs/pitch-rate</input>
   </summer>
   
   <integrator name="Pitch Error Integrator">
      <input>fcs/pitch-rate-error</input>
      <c1>0.25</c1>
   </integrator>
   
   <scheduled_gain name="Scaled Pitch Error">
      <input>fcs/pitch-rate-error</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           0          -0.20
           100        -0.10
           200        -0.08
           500        -0.06
           1000       -0.01
        </tableData>
      </table>
   </scheduled_gain>
   
   <scheduled_gain name="Scaled Pitch Integrator">
      <input>fcs/pitch-error-integrator</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           0          -0.20
           100        -0.10
           200        -0.08
           500        -0.06
           1000       -0.01
        </tableData>
      </table>
   </scheduled_gain>
   
   <summer name="Pitch Output">
      <input>fcs/scaled-pitch-error</input>
      <input>fcs/scaled-pitch-integrator</input>
      <clipto>
         <min>-1.0</min>
         <max>1.0</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-output</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>
   
   <pure_gain name="Target Roll Rate">
      <input>fcs/roll-trim-sum</input>
      <gain>270</gain>
   </pure_gain>
   
   <pure_gain name="Roll Rate">
      <input>velocities/p-rad_sec</input>
      <gain>-57.3</gain>
   </pure_gain>
   
   <summer name="Roll Rate Error">
      <input>fcs/target-roll-rate</input>
      <input>fcs/roll-rate</input>
   </summer>
   
   <integrator name="Roll Error Integrator">
      <input>fcs/roll-rate-error</input>
      <c1>0.25</c1>
   </integrator>
   
   <scheduled_gain name="Scaled Roll Error">
      <input>fcs/roll-rate-error</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           0          0.15
           100        0.08
           200        0.06
           500        0.05
           1000       0.04
        </tableData>
      </table>
   </scheduled_gain>
   
   <scheduled_gain name="Scaled Roll Integrator">
      <input>fcs/roll-error-integrator</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           0          0.10
           100        0.07
           200        0.05
           500        0.04
           1000       0.03
        </tableData>
      </table>
   </scheduled_gain>
   
   <summer name="Roll Output">
      <input>fcs/scaled-roll-error</input>
      <input>fcs/scaled-roll-integrator</input>
      <clipto>
         <min>-1.0</min>
         <max>1.0</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Left Aileron Control">
      <input>fcs/roll-output</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-output</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>
   
   <pure_gain name="Target Yaw Rate">
      <input>fcs/rudder-command-sum</input>
      <gain>15</gain>
   </pure_gain>
   
   <pure_gain name="Yaw Rate">
      <input>velocities/r-rad_sec</input>
      <gain>57.3</gain>
   </pure_gain>
   
   <summer name="Yaw Rate Error">
      <input>fcs/target-yaw-rate</input>
      <input>fcs/yaw-rate</input>
   </summer>
   
   <integrator name="Yaw Error Integrator">
      <input>fcs/yaw-rate-error</input>
      <c1>0.25</c1>
   </integrator>
   
   <scheduled_gain name="Scaled Yaw Error">
      <input>fcs/yaw-rate-error</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           0          0.15
           100        0.07
           200        0.05
           500        0.03
           1000       0.02
        </tableData>
      </table>
   </scheduled_gain>
   
   <scheduled_gain name="Scaled Yaw Integrator">
      <input>fcs/yaw-error-integrator</input>
      <table>
        <independentVar lookup="row">velocities/ve-kts</independentVar>
        <tableData>
           0          0.20
           100        0.10
           200        0.08
           500        0.05
           1000       0.03
        </tableData>
      </table>
   </scheduled_gain>
   
   <summer name="Yaw Output">
      <input>fcs/scaled-yaw-error</input>
      <input>fcs/scaled-yaw-integrator</input>
      <clipto>
         <min>-1.0</min>
         <max>1.0</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/yaw-output</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>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -1.75 -0.5 
              -1.60 -0.0
              -0.80 -0.8
              -0.45 -0.6
              -0.29 -0.8
               0.00 0.1
               0.46 1.5
               0.55 1.2
               0.80 1.6
               1.55 0.0
               1.70 0.5
            </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>fcs/flap-pos-deg</property>
           <value> 0.01167 </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</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/elevator-pos-rad</property>
           <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>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -3.14    0.050
             -1.57    1.500
             -0.40    0.450
             -0.27    0.028
              0.00    0.022
              0.34    0.034
              0.46    0.040
              0.60    0.450
              1.57    1.500
              3.14    0.050
            </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>0.16</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
                0.70      0.000
                0.85      0.002
                1.05      0.018
                1.20      0.011
                1.80      0.009
                2.50      0.008
            </tableData>
          </table>
        </product>
    </function>
    
    <function name="aero/coefficient/CDimach">
       <description>Drag_due_to_mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/cl-squared</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.85      0.000
                1.05      0.020
                1.20      0.010
                1.80      0.008
                2.50      0.007
            </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>
           <value> 0.00250 </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>0.02</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>0.024</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>0.05</value>
       </product>
    </function>
    
    <function name="aero/coefficient/CDbc">
       <description>Drag_due_to_braking_chute</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>systems/chute/unfurl-norm</property>
           <value>0.63</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>0.03</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>-0.1</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    0.120
              2.0    0.040
            </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>
           <table>
              <independentVar lookup="row">velocities/mach</independentVar>
                <tableData>
                  0.0    0.2
                  0.9    0.15
                  2.5   -0.5
                </tableData>
           </table>
       </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     -1.000
              2.0     -0.600
            </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>-18</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>-9</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>-0.40</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>