F4E-2b.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F4E" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Aeromatic v 0.9 </author>
  <filecreationdate> 31 Mar 2006 </filecreationdate>
  <version> 0.1 </version>
  <description>McDonnell F-4 Phantom II</description>
 </fileheader>

<!--
  File:     F4E.xml
  Inputs:
    name:          F4E
    type:          two-engine transonic/supersonic fighter
    max weight:    61795 lb
    wing span:     38.62 ft
    length:        63 ft
    wing area:     530 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  116.59 lb/sq-ft
    CL-alpha:      3.6 per radian
    CL-0:          0.08
    CL-max:        1
    CD-0:          0.024
    K:             0.09
  Changes:
    rkj: thrusters pitched to 5.25 degrees
    rkj: Chord changed to 16.04
    rkj: main gears spread 135.8 inches, nose gear moved aft 99 inches
    rkj: adjusted fuel tank quantities, still need to accurately locate
    rkj: lightened AC_EMPTYWT from 37077 to 33000
    rkj: EYEPTLOC  151.2 0.0 38.0 -> 453.6 0.0 0.0 
    rkj: adjust htailarea, vtailarea
    rkj: adjust AERORP aft 12 inches

-->



 <metrics>
   <wingarea  unit="FT2">  530.00 </wingarea>
   <wingspan  unit="FT" >   38.67 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   16.04 </chord>
   <htailarea unit="FT2">   94.70 </htailarea>
   <htailarm  unit="FT" >   25.20 </htailarm>
   <vtailarea unit="FT2">   67.50 </vtailarea>
   <vtailarm  unit="FT" >   25.20 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 309.20 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 122.20 </x>
     <y>   0.00 </y>
     <z>  61.40 </z>
   </location>
   <location name="VRP" unit="IN">
     <x> 309.20</x>
     <y>0</y>
     <z>16.4</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">     23668 </ixx>
   <iyy unit="SLUG*FT2">    117500 </iyy>
   <izz unit="SLUG*FT2">    133726 </izz>
   <ixy unit="SLUG*FT2">      1573 </ixy>
   <ixz unit="SLUG*FT2">         0 </ixz>
   <iyz unit="SLUG*FT2">         0 </iyz>
   <emptywt unit="LBS" >     33000 </emptywt>
   <location name="CG" unit="IN">
     <x> 309.20 </x>
     <y>   0.00 </y>
     <z>  32.80 </z>
   </location>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 100.00 </x>
     <y>   0.00 </y>
     <z> -90.72 </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">      18538.50 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5179.50 </damping_coeff>
   <max_steer unit="DEG">45.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 350.00 </x>
     <y>-107.50 </y>
     <z> -90.72 </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">      41795.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5359.00 </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> 350.00 </x>
     <y> 107.50 </y>
     <z> -90.72 </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">      41795.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  5359.00 </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> 400.00 </x>
     <y> -19.31 </y>
     <z>   0.00 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      61795.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 12359.00 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 400.00 </x>
     <y>  19.31 </y>
     <z>   0.00 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      61795.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 12359.00 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="J79-GE-17-2">
    <location unit="IN">
      <x> 425.00 </x>
      <y> -20.00 </y>
      <z>  12.00 </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> 425.00 </x>
       <y> -20.00 </y>
       <z>  12.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 5.25 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="J79-GE-17-2">
    <location unit="IN">
      <x> 425.00 </x>
      <y>  20.00 </y>
      <z>  12.00 </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> 425.00 </x>
       <y>  20.00 </y>
       <z>  12.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 5.25 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>
<!-- Internal Fuel 1855 gallons*6.6 -->
  <tank type="FUEL" number="0">
     <location unit="IN">
       <x> 309.20 </x>
       <y>   0.00 </y>
       <z>  50.00 </z>
     </location>
     <capacity unit="LBS"> 12243.00 </capacity>
     <contents unit="LBS"> 12243.00 </contents>
  </tank>
<!-- Centerline Tank 600 gallon*6.6 -->
  <tank type="FUEL" number="1">
     <location unit="IN">
       <x> 309.20 </x>
       <y>   0.00 </y>
       <z> -18.00 </z>
     </location>
     <capacity unit="LBS"> 3960.00 </capacity>
     <contents unit="LBS"> 3960.00 </contents>
  </tank>
<!-- Wing tanks 370 gallons*6.6 -->  
  <tank type="FUEL" number="2">
     <location unit="IN">
       <x> 309.20 </x>
       <y> 141.70 </y>
       <z> -18.00 </z>
     </location>
     <capacity unit="LBS"> 2442.00 </capacity>
     <contents unit="LBS">   50.00 </contents>
  </tank>
<!-- Wing tanks 370 gallons*6.6 -->  
  <tank type="FUEL" number="3">
     <location unit="IN">
       <x> 309.20 </x>
       <y>-141.70 </y>
       <z> -18.00 </z>
     </location>
     <capacity unit="LBS"> 2442.00 </capacity>
     <contents unit="LBS">   50.00 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: F4E">
<!--property>fcs/dragchute-cmd-norm</property-->
<property>fcs/dragchute-pos-norm</property>

  <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> -0.30 </min>
        <max>  0.30 </max>
      </range>
      <output>fcs/elevator-pos-rad</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>

  </channel>

  <channel name="Yaw">
   <summer name="Rudder Command Sum">
      <input>fcs/rudder-cmd-norm</input>
      <input>fcs/yaw-trim-cmd-norm</input>
      <limit>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </limit>
   </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>
      <limit>
        <min> -0.1 </min>
        <max>  0.1 </max>
      </limit>
   </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>
      <limit>
        <min> -1 </min>
        <max>  1 </max>
      </limit>
   </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>

  </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="Flaps Position Normalized">
                <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>

    <scheduled_gain name="Scheduled Steer Pos Deg">
        <input>fcs/steer-cmd-norm</input>
        <table>
            <independentVar>velocities/vg-fps</independentVar>
            <tableData>
                10.0        80.0
                50.0        7.5
                150.0       1.0
            </tableData>
        </table>
        <output>fcs/steer-pos-deg</output>
    </scheduled_gain>


  </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>
  <channel name="Dragchute">
   <kinematic name="Dragchute Control">
     <input>/controls/flight/drag-chute</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>     3 </time>
       </setting>
     </traverse>
     <output>fcs/dragchute-pos-norm</output>
   </kinematic>

  </channel>

 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

<!-- INW -->
    <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>
              -0.20 -0.64
               0.00  0.08
                0.0152  0.1333
                0.1036  0.4033
                0.1892  0.6797
                0.2804  0.9301
                0.3709  1.0146
                0.4549  0.9724
                0.5452  1.0276
                0.6295  1.0309
                0.7051  1.0504
              1.30  0.05  
            </tableData>
          </table>
      </product>
    </function>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>-0.05</value>
       </product>
    </function>

<!-- Fix This -->
    <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">

<!-- Fix This -->
    <function name="aero/coefficient/CDdc">
       <description>Drag_due_to_drag_chute</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/dragchute-pos-norm</property>
           <value>1.034</value>
         </product>
    </function>

<!-- Fix This -->
    <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>
             -1.57       1.500
             -0.26    0.031
              0.00    0.024
              0.26    0.031
              1.57       1.500
            </tableData>
          </table>
       </product>
    </function>

<!-- Fix This -->
    <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>0.09</value>
         </product>
    </function>

<!-- Fix This -->
    <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
                0.81      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>0.034</value>
         </product>
    </function>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <function name="aero/coefficient/CDde">
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-norm</property>
           <value>0.04</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

<!-- Fix This -->
    <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">

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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">

<!-- INW -->
    <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>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
              -1.000   0.0300
                0.0243  -0.0246
                0.1109  -0.0361
                0.2005  -0.0426
                0.2871  -0.0541
                0.3594  -0.0541
                0.4633  -0.0738
                0.5527  -0.0918
                0.6214  -0.1410
                0.7217  -0.2033
               1.0000  -0.5
            </tableData>
          </table>
      </product>
    </function>

<!-- Fix This -->
    <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     -0.800
              2.0     -0.200
            </tableData>
          </table>
       </product>
    </function>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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">

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>

<!-- Fix This -->
    <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>