DC-6B-jsb.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="DC-6B" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author>Syd Adams</author>
  <filecreationdate> 2008-08-27 </filecreationdate>
  <version>1.0</version>
  <description> Douglas DC-6B. </description>
 </fileheader>

<!--
  Specs:

Douglas DC-6 specs
Length: 32.18 m
Wingspan : 35.81 m
Height : 8.66
Empty Wgt: 55,357 lbs
Max TO wgt: 107,000 lbs

Powerplant : 4x PW R-2800 CB-17 2500 hp
Displacement: 2804 cu
Bore: 5.75
Stroke : 6
Dry Weight : 2360 lbs
Prop gear reduction ratio : 0.45:1
Low impeller gear ratio 7.29:1
High impeller gear ratio 8.58:1


TO HP:2500 ... RPM 2800 MP inHG 60.0
Props : Hamilton Standard 43E60 / 6895
Cruise 274 kt
Fuel Flow | 10000 ft | kias 185 | 2200 rpm | 520 lbs per hour - per engine
Srv Ceiling: 25000 ft
Rate of climb 1070 fpm
Range 2610 nm

Airspeed Limits :
Vc 261 kts SL to 15000 ft
Vf : 0 - 30 deg 174 kts
    30 - 50 deg 139 kts
    Vlo 174 kts

landing 76 kts w flaps
stall 94 kts no flaps

NACA 23016 root
NACA 23012 tip
Datum 63 in (1.6002 m) aft of nose
L.E.MAC 163.6 in (4.15544 m)

  File:     DC-6B.xml
  Inputs:
    name:          DC-6B
    type:          multi-engine prop transport
    max weight:    97304.445 lb
    wing span:     117.49261 ft
    length:        105.58258 ft
    wing area:     1462.9635 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   piston
    engine layout: wings
    yaw damper?    no

  Outputs:
    wing loading:  66.51 lb/sq-ft
    CL-alpha:      4.9 per radian
    CL-0:          0.24
    CL-max:        1.4
    CD-0:          0.025
    K:             0.039

-->

 <metrics>
   <wingarea  unit="M2"> 135.90 </wingarea>
   <wingspan  unit="M"> 35.81</wingspan>
   <wing_incidence>2.00</wing_incidence>
   <chord     unit="M"> 3.795</chord>
   <htailarea unit="M2">71.344</htailarea>
   <htailarm  unit="M">16.09</htailarm>
   <vtailarea unit="M2">80.262</vtailarea>
   <vtailarm  unit="M">16.09</vtailarm>
   <location name="AERORP" unit="M">
     <x>-0.396</x>
     <y>0.00</y>
     <z>0.00</z>
   </location>
   <location name="EYEPOINT" unit="M">
     <x>-9.143</x>
     <y>-0.609</y>
     <z>1.340</z>
   </location>
   <location name="VRP" unit="M">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">640751</ixx>
   <iyy unit="SLUG*FT2">618997</iyy>
   <izz unit="SLUG*FT2">1245680</izz>
   <emptywt unit="LBS" >58383</emptywt>
   <location name="CG" unit="M">
     <x>-0.396</x>
     <y>0.00</y>
     <z> -0.804</z>
   </location>
    <pointmass name="crew">
        <weight unit="LBS">400</weight>
        <location name="POINTMASS" unit="M">
        <x>9.143</x>
        <y>0</y>
        <z>0</z>
        </location>
    </pointmass>
    <pointmass name="cargo">
        <weight unit="LBS">12800</weight><!-- 64 passengers-->
        <location name="POINTMASS" unit="M">
        <x>-0.396</x>
        <y>0</y>
        <z>0</z>
        </location>
    </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="M">
     <x>-9.382</x>
     <y>0.00</y>
     <z> -3.075</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">      29191.33 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">  9730.44 </damping_coeff>
   <max_steer unit="DEG">30.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>RETRACT</retractable>
 </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="M">
     <x>0.248</x>
     <y>-3.939</y>
     <z> -2.949</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">      97304.45 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 19460.89 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>RETRACT</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN">
   <location unit="M">
     <x>0.248</x>
     <y>3.939</y>
     <z>-2.949</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">      97304.45 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 19460.89 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>RETRACT</retractable>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="M">
     <x>0</x>
     <y>17.85</y>
     <z>1.431</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">97304.45 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">19460.89 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="M">
     <x>0</x>
     <y>-17.85</y>
     <z>1.431</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">97304.45 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">19460.89 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="TAIL">
    <location unit="M">
     <x>19.0</x>
     <y>0.0</y>
     <z>0.35</z>
    </location>
    <static_friction>0.80</static_friction>
    <dynamic_friction>0.50</dynamic_friction>
    <spring_coeff unit="LBS/FT">97304.45 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">19460.89 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="eng_R-2800">
    <location unit="M">
      <x>-0.396</x>
      <y>-8.070</y>
      <z>0.244</z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <feed>3</feed>
    <thruster file="prop_RAF-6-mod">
     <location unit="M">
       <x>-0.396</x>
      <y>-8.070</y>
      <z>0.244</z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="eng_R-2800">
    <location unit="M">
       <x>-0.396</x>
      <y>-3.851</y>
      <z>-0.092</z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>1</feed>
    <feed>2</feed>
    <feed>3</feed>
    <thruster file="prop_RAF-6-mod">
     <location unit="M">
       <x>-0.396</x>
      <y>-3.851</y>
      <z>-0.092</z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="eng_R-2800">
    <location unit="M">
       <x>-0.396</x>
      <y>3.851</y>
      <z>-0.092</z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>4</feed>
    <feed>5</feed>
    <feed>6</feed>
    <feed>7</feed>
    <thruster file="prop_RAF-6-mod">
     <location unit="M">
       <x>-0.396</x>
      <y>3.851</y>
      <z>-0.092</z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <engine file="eng_R-2800">
    <location unit="M">
      <x>-0.396</x>
      <y>8.070</y>
      <z>0.244</z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>4</feed>
    <feed>5</feed>
    <feed>6</feed>
    <feed>7</feed>
    <thruster file="prop_RAF-6-mod">
     <location unit="M">
       <x>-0.396</x>
      <y>8.070</y>
      <z>0.244</z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

<!-- Eight Wing Tank Airplane - 5512 Gallon System: (usable)
2 outer wing tanks (#1 and #4 main) 695 gal. ea.
2 inboard inner wing tanks (#2 and #3 main) 713 gal. ea. (+451.0)
2 outboard inner wing tanks (#1 and #4 alt.) 576 gal. ea. (+452.0)
2 inner wing fuel cells (#2 and #3 alt.) 762 gal. ea. (+468.0)
-->
  <tank type="FUEL" number="0"><!-- #1 main-->
     <location unit="M">
       <x>-0.396</x>
       <y>-13.35</y>
       <z>0.910</z>
     </location>
     <capacity unit="LBS"> 4170</capacity>
     <contents unit="LBS"> 2000</contents>
  </tank>

  <tank type="FUEL" number="1"><!-- #2 main-->
     <location unit="M">
       <x>-0.396</x>
       <y>-6.168</y>
       <z>0.045</z>
     </location>
     <capacity unit="LBS">4314 </capacity>
     <contents unit="LBS">2000</contents>
  </tank>

  <tank type="FUEL" number="2"><!-- #1 alt-->
     <location unit="M">
       <x>-0.396</x>
       <y>-10.15</y>
       <z>0.530</z>
     </location>
     <capacity unit="LBS">3480</capacity>
     <contents unit="LBS"> 2000</contents>
  </tank>

  <tank type="FUEL" number="3"><!-- #2 alt-->
     <location unit="M">
       <x>-0.396</x>
       <y>-2.265</y>
       <z>-0.43</z>
     </location>
     <capacity unit="LBS"> 4572</capacity>
     <contents unit="LBS">2000</contents>
  </tank>

  <tank type="FUEL" number="4"><!-- #3 alt-->
     <location unit="M">
       <x>-0.396</x>
       <y>2.265</y>
       <z>-0.43</z>
     </location>
     <capacity unit="LBS">4572</capacity>
     <contents unit="LBS">2000</contents>
  </tank>

  <tank type="FUEL" number="5"><!-- #4 alt-->
     <location unit="M">
       <x>-0.396</x>
       <y>10.15</y>
       <z>0.530</z>
     </location>
     <capacity unit="LBS">3480</capacity>
     <contents unit="LBS">2000</contents>
  </tank>

  <tank type="FUEL" number="6"><!-- #3 main-->
     <location unit="M">
       <x>-0.396</x>
       <y>6.168</y>
       <z>0.045</z>
     </location>
     <capacity unit="LBS">4314</capacity>
     <contents unit="LBS">2000</contents>
  </tank>

  <tank type="FUEL" number="7"><!-- #4 main-->
     <location unit="M">
       <x>-0.396</x>
       <y>13.35</y>
       <z>0.910</z>
     </location>
     <capacity unit="LBS">4170</capacity>
     <contents unit="LBS">2000</contents>
  </tank>


 </propulsion>

 <flight_control name="FCS: DC-6B">

  <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> -0.36 </min>
        <max>  0.36 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.36 </min>
        <max>  0.36 </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> -0.33</min>
        <max>  0.33 </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> -0.33 </min>
        <max>  0.33 </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>-0.33 </min>
        <max>0.33 </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>-0.33 </min>
        <max>0.33 </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>-1</min>
        <max>1</max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-command-sum</input>
      <range>
        <min>-0.26</min>
        <max>0.26</max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>fcs/rudder-pos-rad</input>
      <domain>
        <min>-0.26</min>
        <max>0.26</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>10</position>
          <time>2</time>
       </setting>
       <setting>
          <position>20</position>
          <time>2</time>
       </setting>
       <setting>
          <position>30</position>
          <time>2</time>
       </setting>
       <setting>
          <position>40</position>
          <time>2</time>
       </setting>
       <setting>
          <position>50</position>
          <time>2</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>50</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>

</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>
              -0.20 -0.540
               0.00 0.50
             0.24    1.600
               0.60 0.604
            </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> 0.07000 </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>0.22</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>
             -1.57       1.400
             -0.26    0.030
              0.00    0.020
              0.26    0.030
              1.57       1.400
            </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>0.035</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
                0.7      0.000
                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>
           <value> 0.00117 </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>0.023</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>0.025</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>
           <property>fcs/elevator-pos-norm</property>
           <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>-0.35</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    0.130
              2.0    0.050
            </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>-0.35</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     -1.000
              2.0     -0.250
            </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>-20</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>-0.008</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>