c130j-jsb.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="C-130J" 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 0.95 </author>
  <filecreationdate> 2011-12-10 </filecreationdate>
  <version>$Revision: 1.10 $</version>
  <description> Models a C-130J. </description>
 </fileheader>

<!--
  File:     C-130J.xml
  Inputs:
    name:          C-130J
    type:          four-engine transonic transport
    max weight:    155029.14 lb
    wing span:     132.58521 ft
    length:        97.74099 ft
    wing area:     1745.2218 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     4
    engine type:   turboprop
    engine layout: wings
    yaw damper?    no

  Outputs:
    wing loading:  88.83 lb/sq-ft
    CL-alpha:      4.4 per radian
    CL-0:          0.2
    CL-max:        1.2
    CD-0:          0.017
    K:             0.042

-->

 <metrics>
   <wingarea  unit="FT2"> 1745.22 </wingarea>
   <wingspan  unit="FT" >  132.59 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   13.16 </chord>
   <htailarea unit="FT2">  436.31 </htailarea>
   <htailarm  unit="FT" >   43.98 </htailarm>
   <vtailarea unit="FT2">  349.04 </vtailarea>
   <vtailarm  unit="FT" >   43.98 </vtailarm>
   <location name="AERORP" unit="M">
     <x>  -0.46</x>
     <y>   0.0 </y>
     <z>   4.2 </z>
   </location>
   <location name="EYEPOINT" unit="M">
     <x> -10.6 </x>
     <y>  -0.5 </y>
     <z>   3.56 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    894185 </ixx>
   <iyy unit="SLUG*FT2">    787734 </iyy>
   <izz unit="SLUG*FT2">   1578631 </izz>
   <emptywt unit="LBS" >     81500 </emptywt>
   <location name="CG" unit="M">
     <x>  -0.56</x>
     <y>   0.0 </y>
     <z>   3.8 </z>
   </location>
   <pointmass name="Cargo">
    <form shape="cylinder">
       <radius unit="M"> 1.25 </radius>
       <length unit="M"> 2.5 </length>
    </form>
    <weight unit="KG">0</weight>
    <location unit="M">
        <x> 3.4 </x>
        <y> 0 </y>
        <z> 2.3 </z>
    </location>
    </pointmass>
 </mass_balance>

 <ground_reactions>
<contact name="MLG Axis.l1" type="BOGEY">
   <location unit="M">
    <x>-0.62</x>
		<y>-2.172</y>
		<z>-0.355</z>
   </location>
   <static_friction>0.800</static_friction>
   <dynamic_friction>0.500</dynamic_friction>
   <rolling_friction>0.020</rolling_friction>
   <spring_coeff unit="N/M">824700.000</spring_coeff>
   <damping_coeff type="SQUARE" unit="N/M2/SEC2">120000.000</damping_coeff>
   <damping_coeff_rebound unit="N/M/SEC"> 200000 </damping_coeff_rebound>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
  </contact>
  <contact name="MLG Axis.l2" type="BOGEY">
   <location unit="M">
    <x>0.91</x>
		<y>-2.172</y>
		<z>-0.355</z>
   </location>
   <static_friction>0.800</static_friction>
   <dynamic_friction>0.500</dynamic_friction>
   <rolling_friction>0.020</rolling_friction>
   <spring_coeff unit="N/M">824700.000</spring_coeff>
   <damping_coeff type="SQUARE" unit="N/M2/SEC2">120000.000</damping_coeff>
   <damping_coeff_rebound unit="N/M/SEC"> 200000 </damping_coeff_rebound>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
  </contact>
  <contact name="MLG Axis.r1" type="BOGEY">
   <location unit="M">
    <x>-0.62</x>
		<y>2.172</y>
		<z>-0.355</z>
   </location>
   <static_friction>0.800</static_friction>
   <dynamic_friction>0.500</dynamic_friction>
   <rolling_friction>0.020</rolling_friction>
   <spring_coeff unit="N/M">824700.000</spring_coeff>
   <damping_coeff type="SQUARE" unit="N/M2/SEC2">120000.000</damping_coeff>
   <damping_coeff_rebound unit="N/M/SEC"> 200000 </damping_coeff_rebound>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
  </contact>
  <contact name="MLG Axis.r2" type="BOGEY">
   <location unit="M">
    <x>0.91</x>
		<y>2.172</y>
		<z>-0.355</z>
   </location>
   <static_friction>0.800</static_friction>
   <dynamic_friction>0.500</dynamic_friction>
   <rolling_friction>0.020</rolling_friction>
   <spring_coeff unit="N/M">824700.000</spring_coeff>
   <damping_coeff type="SQUARE" unit="N/M2/SEC2">120000.000</damping_coeff>
   <damping_coeff_rebound unit="N/M/SEC"> 200000 </damping_coeff_rebound>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
  </contact>
  <contact name="NLG-Wheel-Axis" type="BOGEY">
   <location unit="M">
    <x>-9.63</x>
    <y>-0.0</y>
    <z>-0.275</z>
   </location>
   <static_friction>1.800</static_friction>
   <dynamic_friction>0.900</dynamic_friction>
   <rolling_friction>0.020</rolling_friction>
   <spring_coeff unit="N/M">180000.000</spring_coeff>
   <damping_coeff unit="N/M/SEC">90000.000</damping_coeff>
   <damping_coeff_rebound unit="N/M/SEC"> 90000 </damping_coeff_rebound>
   <max_steer unit="DEG">20</max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
  </contact>
  <contact name="NLG-Wheel-Axis-Stop" type="BOGEY">
   <location unit="M">
    <x>-9.63</x>
    <y>-0.0</y>
    <z>-0.005</z>
   </location>
   <static_friction>0</static_friction>
   <dynamic_friction>0</dynamic_friction>
   <rolling_friction>0</rolling_friction>
   <spring_coeff unit="N/M">72000000</spring_coeff>
   <damping_coeff type="SQUARE" unit="N/M2/SEC2">180000</damping_coeff>
   <damping_coeff_rebound unit="N/M/SEC">36000000</damping_coeff_rebound>
  </contact>
  
  <contact type="STRUCTURE" name="Ramp.l">
    <location unit="M">
     <x> 8.13 </x>
     <y> -0.3 </y>
     <z> 0.6 </z>
    </location>
    <static_friction>  4 </static_friction>
    <dynamic_friction> 2.5 </dynamic_friction>
    <spring_coeff unit="N/M">72000000</spring_coeff>
    <damping_coeff unit="N/M/SEC">80000</damping_coeff>
    <damping_coeff_rebound unit="N/M/SEC">72000000</damping_coeff_rebound>
 </contact>
 <contact type="STRUCTURE" name="Ramp.r">
    <location unit="M">
     <x> 8.13 </x>
     <y> 0.3 </y>
     <z> 0.6 </z>
    </location>
    <static_friction>  4 </static_friction>
    <dynamic_friction> 2.5 </dynamic_friction>
    <spring_coeff unit="N/M">72000000</spring_coeff>
    <damping_coeff unit="N/M/SEC">80000</damping_coeff>
    <damping_coeff_rebound unit="N/M/SEC">72000000</damping_coeff_rebound>
 </contact>
  
<!--  <contact type="BOGEY" name="NOSE">
   <location unit="M">
     <x>  -19.630 </x>
     <y>   0.000 </y>
     <z>  -0.275 </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">      46508.74 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 15502.91 </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="M">
     <x>  -0.831 </x>
     <y>  2.125 </y>
     <z> -0.275 </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">      155029.14 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 31005.83 </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>  -0.831 </x>
     <y> -2.125 </y>
     <z> -0.275 </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">      155029.14 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 31005.83 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>
 
 <contact type="BOGEY" name="LEFT_MAIN_A">
   <location unit="M">
     <x> 0.702 </x>
     <y>  2.125 </y>
     <z> -0.275 </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">      155029.14 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 31005.83 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>LEFT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="RIGHT_MAIN_A">
   <location unit="M">
     <x> 0.702 </x>
     <y> -2.125 </y>
     <z> -0.275 </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">      155029.14 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 31005.83 </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> 645.09 </x>
     <y> -66.29 </y>
     <z> -29.32 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      155029.14 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 31005.83 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 645.09 </x>
     <y>  66.29 </y>
     <z> -29.32 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      155029.14 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 31005.83 </damping_coeff>
 </contact>
-->

  <contact type="STRUCTURE" name="Wing.l">
    <location unit="M">
     <x> -0.83 </x>
     <y>-20.19 </y>
     <z>  4.83 </z>
    </location>
    <static_friction>  4 </static_friction>
    <dynamic_friction> 2.5 </dynamic_friction>
    <spring_coeff unit="N/M">72000000</spring_coeff>
    <damping_coeff unit="N/M/SEC">80000</damping_coeff>
    <damping_coeff_rebound unit="N/M/SEC">72000000</damping_coeff_rebound>
  </contact>
  <contact type="STRUCTURE" name="Wing.r">
    <location unit="M">
     <x> -0.83 </x>
     <y> 20.19 </y>
     <z>  4.83 </z>
    </location>
    <static_friction>  4 </static_friction>
    <dynamic_friction> 2.5 </dynamic_friction>
    <spring_coeff unit="N/M">72000000</spring_coeff>
    <damping_coeff unit="N/M/SEC">80000</damping_coeff>
    <damping_coeff_rebound unit="N/M/SEC">72000000</damping_coeff_rebound>
  </contact>
 </ground_reactions>

 <propulsion>

  <engine file="Rolls-Royce AE 2100">
    <location unit="M">
      <x> -4.0 </x>
      <y> -5.15 </y>
      <z>  3.7 </z>
    </location>
    <feed>1</feed>
    <thruster file="prop">
     <location unit="M">
      <x> -4.0 </x>
      <y> -5.15 </y>
      <z>  3.7 </z>
     </location>
     <orient unit="DEG">
       <roll>0</roll>
       <pitch>0</pitch>
       <yaw>0</yaw>
     </orient>
    </thruster>
  </engine>

  <engine file="Rolls-Royce AE 2100">
    <location unit="M">
      <x> -4.0 </x>
      <y>  5.15 </y>
      <z>  3.7 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>2</feed>
    <thruster file="prop">
     <location unit="M">
      <x> -4.0 </x>
      <y>  5.15 </y>
      <z>  3.7 </z>
     </location>
     <orient unit="DEG">
       <roll>0</roll>
       <pitch>0</pitch>
       <yaw>0</yaw>
     </orient>
    </thruster>
  </engine>

  <engine file="Rolls-Royce AE 2100">
    <location unit="M">
      <x> -4.0 </x>
      <y>-10.3 </y>
      <z>  3.9 </z>
    </location>
    <feed>3</feed>
    <thruster file="prop">
     <location unit="M">
      <x> -4.0 </x>
      <y>-10.3 </y>
      <z>  3.9 </z>
     </location>
     <orient unit="DEG">
       <roll>0</roll>
       <pitch>0</pitch>
       <yaw>0</yaw>
     </orient>
    </thruster>
  </engine>

  <engine file="Rolls-Royce AE 2100">
    <location unit="M">
      <x> -4.0 </x>
      <y> 10.3 </y>
      <z>  3.9 </z>
    </location>
    <feed>0</feed>
    <thruster file="prop">
     <location unit="M">
      <x> -4.0 </x>
      <y> 10.3 </y>
      <z>  3.9 </z>
     </location>
     <orient unit="DEG">
       <roll>0</roll>
       <pitch>0</pitch>
       <yaw>0</yaw>
     </orient>
    </thruster>
  </engine>
  <!--
  <engine file="GTCP85-180L">
    <location unit="M">
      <x> -2.0 </x>
      <y> -2.3 </y>
      <z>  1.5 </z>
    </location>
    <feed>2</feed>
    <thruster file="alternator"/>
  </engine>
-->
  <tank type="FUEL" number="0">
     <location unit="M">
       <x> -0.3 </x>
       <y> -3.6 </y>
       <z>  4.2 </z>
     </location>
     <capacity unit="LBS"> 8000 </capacity>
     <contents unit="LBS"> 4000 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <location unit="M">
       <x> -0.2 </x>
       <y> -7.8 </y>
       <z>  4.2 </z>
     </location>
     <capacity unit="LBS"> 8000 </capacity>
     <contents unit="LBS"> 4000 </contents>
  </tank>

  <tank type="FUEL" number="2">
     <location unit="M">
       <x> -0.3 </x>
       <y>  3.6 </y>
       <z>  4.2 </z>
     </location>
     <capacity unit="LBS"> 8000 </capacity>
     <contents unit="LBS"> 4000 </contents>
  </tank>

  <tank type="FUEL" number="3">
     <location unit="M">
       <x> -0.2 </x>
       <y>  7.8 </y>
       <z>  4.2 </z>
     </location>
     <capacity unit="LBS"> 8000 </capacity>
     <contents unit="LBS"> 4000 </contents>
  </tank>

 </propulsion>

 <flight_control name="FCS: C-130J">

  <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>
      <output>fcs/elevator-pos-norm</output>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <range>
        <min> -0.729 </min>
        <max>  0.231 </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>

   <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> -1 </min>
        <max>  1 </max>
      </clipto>
      <output>fcs/rudder-pos-norm</output>
    </summer>

    <aerosurface_scale name="Rudder Control">
        <input>fcs/rudder-pos-norm</input>
        <range>
            <min>-0.436</min>
            <max>0.436</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> 18 </position>
          <time>      7 </time>
       </setting>
       <setting>
          <position> 36 </position>
          <time>      5 </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> 36 </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>    19 </time>
       </setting>
     </traverse>
     <output>gear/gear-pos-norm</output>
   </kinematic>
  </channel>

 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

    <function name="aero/force/Lift_less_elevator">
      <description>Lift due to alpha and flaps</description>
      <product>
        <property>aero/qbar-psf</property>
        <property>metrics/Sw-sqft</property>
        <sum name="aero/coefficient/CL">
          <table name="aero/coefficient/CLalpha">
            <independentVar lookup="row">aero/alpha-deg</independentVar>
            <tableData>
              -12   -0.98
                5    0.87
               12    1.49
               16    1.76
               18    1.83
               19.2  1.85
               21    1.83
               22.5  1.75
               23.5  1.6
            </tableData>
          </table>
          <table name="aero/coefficient/CLflap">
            <independentVar lookup="row">fcs/flap-pos-deg</independentVar>
            <tableData>
               0  0
              18  0.44
              36  1.2
            </tableData>
          </table>
        </sum>
      </product>
    </function>

    <function name="aero/force/Lift_elevator">
       <description>Lift due to Elevator Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-rad</property>
           <value>0.2</value>
       </product>
    </function>

  </axis>

  <axis name="DRAG">

    <function name="aero/force/Drag_basic">
       <description>Drag at zero lift</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
             -1.57       1.500
             -0.26    0.022
              0.00    0.017
              0.26    0.022
              1.57       1.500
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_induced">
       <description>Induced drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.042</value>
         </product>
    </function>

    <function name="aero/force/Drag_mach">
       <description>Drag due to mach</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
                0.00      0.000
                0.79      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

    <function name="aero/force/Drag_flap">
       <description>Drag due to flaps</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/flap-pos-deg</property>
           <value> 0.0009 </value>
         </product>
    </function>

    <function name="aero/force/Drag_gear">
       <description>Drag due to gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.011</value>
         </product>
    </function>

    <function name="aero/force/Drag_beta">
       <description>Drag due to sideslip</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <tableData>
              -1.57       1.230
              -0.26    0.050
               0.00       0.000
               0.26    0.050
               1.57       1.230
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/force/Drag_elevator">
       <description>Drag due to Elevator Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <abs><property>fcs/elevator-pos-norm</property></abs>
           <value>0.04</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/force/Side_beta">
       <description>Side force due to beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/beta-rad</property>
           <value>-1</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/moment/Roll_beta">
       <description>Roll moment due to beta (dihedral effect)</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-deg</property>
           <value>-0.0015</value>
       </product>
    </function>

    <function name="aero/moment/Roll_damp">
       <description>Roll moment due to roll rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/p-aero-rad_sec</property>
           <value>-0.4</value>
       </product>
    </function>

    <function name="aero/moment/Roll_yaw">
       <description>Roll moment due to yaw rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>0.15</value>
       </product>
    </function>

    <function name="aero/moment/Roll_aileron">
       <description>Roll moment due to aileron</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.100
              2.0    0.033
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Roll_rudder">
       <description>Roll moment due to rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>0.003</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/moment/Pitch_alpha">
       <description>Pitch moment due to alpha</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/alpha-rad</property>
           <value>-1.1</value>
       </product>
    </function>

<!--
    <function name="aero/moment/Pitch_less_elevator">
       <description>Pitch moment due to lift</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <table name="aero/coefficient/Cm25">
             <independentVar lookup="row">aero/coefficient/CL</independentVar>
             <tableData>
              -0.3   0.3
               1.1   0.025
               2.22 -0.35
             </tableData>
           </table>
       </product>
    </function>
-->
    <function name="aero/moment/Pitch_elevator">
       <description>Pitch moment due to elevator</description>
       <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     -1.300
              2.0     -0.325
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/moment/Pitch_damp">
       <description>Pitch moment due to pitch rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/ci2vel</property>
           <property>velocities/q-aero-rad_sec</property>
           <value>-21</value>
       </product>
    </function>

    <function name="aero/moment/Pitch_alphadot">
       <description>Pitch moment due to alpha rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/cbarw-ft</property>
           <property>aero/ci2vel</property>
           <property>aero/alphadot-rad_sec</property>
           <value>-4</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <function name="aero/moment/Yaw_beta">
       <description>Yaw moment due to beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/beta-rad</property>
           <value>0.12</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_damp">
       <description>Yaw moment due to yaw rate</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/bi2vel</property>
           <property>velocities/r-aero-rad_sec</property>
           <value>-0.15</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_rudder">
       <description>Yaw moment due to rudder</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.05</value>
       </product>
    </function>

    <function name="aero/moment/Yaw_aileron">
       <description>Adverse yaw</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/left-aileron-pos-rad</property>
           <value>0</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>