J-11A.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Su-27SK" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Yanes Bechir based on Aeromatic 0.95 output </author>
  <filecreationdate>2016-08-23</filecreationdate>
  <version>$Revision: 0.03 $</version>
  <description> Models a Su-27SKM. </description>
 </fileheader>

<!--
  File:     Su-27SK.xml
  Inputs:
    name:          Su-27SK
    type:          two-engine transonic/supersonic fighter
    max weight:    67142.25 lb
    wing span:     48.2307 ft
    length:        71.8539 ft
    wing area:     667.427582 sq-ft
    gear type:     tricycle
    retractable?:  yes
    # engines:     2
    engine type:   turbine
    engine layout: aft fuselage
    yaw damper?    yes
  Outputs:
    wing loading:  100.60 lb/sq-ft
    payload:       17125.9 lbs
    CL-alpha:      3.6 per radian
    CL-0:          0.08
    CL-max:        1
    CD-0:          0.024
    K:             0.12

-->

 <metrics>
   <wingarea  unit="FT2">  667.43 </wingarea>
   <wingspan  unit="FT" >   48.23 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >   13.84 </chord>
   <htailarea unit="FT2">  133.49 </htailarea>
   <htailarm  unit="FT" >   28.74 </htailarm>
   <vtailarea unit="FT2">  120.14 </vtailarea>
   <vtailarm  unit="FT" >   28.74 </vtailarm>
   <location name="AERORP" unit="IN">
     <x> 517.35 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x> 172.45 </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">     54859 </ixx>
   <iyy unit="SLUG*FT2">    167365 </iyy>
   <izz unit="SLUG*FT2">    169937 </izz>
   <emptywt unit="LBS" >     36118 </emptywt>
   <location name="CG" unit="IN">
     <x> 517.35 </x>
     <y>   0.00 </y>
     <z> -21.56 </z>
   </location>
******************************************************************

   <pointmass name="pylon0-load">
    <description> Weapon mass at pylon n:1</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>11.55</x>
      <y> 0.00 </y>
      <z>-0.404 </z>
    </location>
  </pointmass>
  
   <pointmass name="pylon1-load">
    <description> Weapon mass at pylon n:2</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>16.00</x>
      <y> 0.00 </y>
      <z>-0.404 </z>
    </location>
  </pointmass>
  
  <pointmass name="pylon2-load">
    <description> Weapon mass at pylon n:3</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>14.000</x>
      <y>-4.836</y>
      <z>-0.24 </z>
    </location>
  </pointmass>
  <pointmass name="pylon3-load">
    <description> Weapon mass at pylon n:4</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>14.000</x>
      <y> 4.836</y>
      <z>-0.240</z>
    </location>
  </pointmass>
  
  <pointmass name="pylon4-load">
    <description> Weapon mass at pylon n:5</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>14.800</x>
      <y>-6.490</y>
      <z>-0.020</z>
    </location>
  </pointmass>
  
  <pointmass name="pylon5-load">
    <description> Weapon mass at pylon n:6</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>14.800</x>
      <y> 6.490</y>
      <z>-0.020</z>
    </location>
  </pointmass>
  
  <pointmass name="pylon6-load">
    <description> Weapon mass at pylon n:7</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>15.400</x>
      <y>-7.570</y>
      <z> 0.156</z>
    </location>
  </pointmass>
  
  <pointmass name="pylon7-load">
    <description> Weapon mass at pylon n:8</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>15.400</x>
      <y> 7.570</y>
      <z> 0.156</z>
    </location>
  </pointmass>
  
  <pointmass name="pylon8-load">
    <description> Weapon mass at pylon n:9</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>13.550</x>
      <y>-1.235</y>
      <z>-1.324</z>
    </location>
  </pointmass>
  
  <pointmass name="pylon9-load">
    <description> Weapon mass at pylon n:10</description>
    <weight unit="KG">0</weight>
    <location name="POINTMASS" unit="M">
      <x>13.550</x>
      <y> 1.235</y>
      <z>-1.324</z>
    </location>
  </pointmass>
  
   <pointmass name="pilot">
    <description> Pilots body</description>
    <weight unit="KG">80</weight>
    <location name="POINTMASS" unit="M">
      <x> 6.55</x>
      <y> 0.00 </y>
      <z>-0.404 </z>
    </location>
  </pointmass>
  
   <pointmass name="Payload">
    <description> 17126 LBS + full (13898 LBS) fuel should bring model up to entered max weight</description>
    <weight unit="LBS">   8563.0 </weight>
    <location name="POINTMASS" unit="IN">
      <x> 517.35 </x>
      <y>   0.00 </y>
      <z> -21.56 </z>
    </location>
  </pointmass> 
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> 112.09 </x>
     <y>   0.00 </y>
     <z> -103.47 </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">      22142.67 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 1400.12 </damping_coeff>
   <max_steer unit="DEG"> 35.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
  </contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 538.04 </x>
     <y> -52.09 </y>
     <z> -103.47 </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">      67142.25 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33571.12 </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> 538.04 </x>
     <y>  52.09 </y>
     <z> -103.47 </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">      67142.25 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 33571.12 </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> 517.35 </x>
     <y> -24.12 </y>
     <z> -21.56 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      67142.25 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 67142.25 </damping_coeff>
  </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> 517.35 </x>
     <y>  24.12 </y>
     <z> -21.56 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 1.00 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      67142.25 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC"> 67142.25 </damping_coeff>
  </contact>

 </ground_reactions>

 <propulsion>

   <engine file="Saturn-AL-31">
    <location unit="IN">
      <x> 802.25 </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> 802.25 </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-AL-31">
    <location unit="IN">
      <x> 802.25 </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> 802.25 </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="GTDE-117_T">   

    <location unit="M">
      <x>  5.0  </x>
      <y>  0.0  </y>
      <z> -0.18 </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="M">
      <x>  5.0  </x>
      <y>  0.0  </y>
      <z> -0.18 </z>
    </location>
     <orient unit="RAD">
       <pitch>  0.0 </pitch>
       <roll>   0.0 </roll>
       <yaw>    0.0 </yaw>
     </orient>
    </thruster>
  </engine>
-->

  <tank type="FUEL" number="0">	<!-- Tank1 fuselage afterproue -->
     <location unit="IN">
       <x> 260.35 </x>
       <y>   0.00 </y>
       <z> -21.56 </z>
     </location>
     <capacity unit="LBS"> 7010.70 </capacity>
     <contents unit="LBS"> 3505.35 </contents>

  </tank>

  <tank type="FUEL" number="1">	<!-- Tank2 Main center fuselage  -->
     <location unit="IN">
       <x> 517.35 </x>
       <y>   0.00 </y>
       <z> -21.56 </z>
     </location>
     <capacity unit="LBS"> 9171.23 </capacity>
     <contents unit="LBS"> 4585.61 </contents>

  </tank>

  <tank type="FUEL" number="2">	<!-- Tank3L L.wing   -->
     <location unit="IN">
       <x> 517.35 </x>
       <y>  -137  </y>
       <z> -21.56 </z>
     </location>
     <capacity unit="LBS"> 1168.45 </capacity>
     <contents unit="LBS"> 584.22 </contents>
     
  </tank>
  
  <tank type="FUEL" number="3">	<!-- Tank3R R.wing   -->
     <location unit="IN">
       <x> 517.35 </x>
       <y>   137  </y>
       <z> -21.56 </z>
     </location>
     <capacity unit="LBS"> 1168.45 </capacity>
     <contents unit="LBS"> 584.22 </contents>

  </tank>
  
  <tank type="FUEL" number="4">	<!-- Tank4 rear fuselage   -->
     <location unit="IN">
       <x> 669.29 </x>
       <y>  0.00  </y>
       <z> -21.56 </z>
     </location>
     <capacity unit="LBS"> 2204.62 </capacity>
     <contents unit="LBS"> 1102.31 </contents>

  </tank>

 </propulsion>
 
<system file="fuel"/>
<system file="SDU-10"/>
 
 <flight_control name="FCS: Su-27SK">
	 
	  <property value="0">systems/engines/emerdisable_afterburning</property>
	  <property value="1">systems/engines/cmd_t_L</property>
	  <property value="1">systems/engines/cmd_t_R</property>
	
  <channel name="Throttle Control">
           
    <scheduled_gain name="Throttle1">
      <input>systems/engines/cmd_t_L</input>
        <table>
          <independentVar>fcs/throttle-cmd-norm[0]</independentVar>
          <tableData>
            0.00    0.0
            0.0685  0.0
            0.072   0.0
            0.828   1.0
            0.832   1.0
            1.00    2.0
          </tableData>
        </table>
      <output>fcs/throttle1-pos-norm</output>
    </scheduled_gain>
    <scheduled_gain name="Throttle2">
      <input>systems/engines/cmd_t_R</input>
        <table>
          <independentVar>fcs/throttle-cmd-norm[1]</independentVar>
          <tableData>
            0.00    0.0
            0.0685  0.0
            0.072   0.0
            0.828   1.0
            0.832   1.0
            1.00    2.0
          </tableData>
        </table>
      <output>fcs/throttle2-pos-norm</output>
    </scheduled_gain>

   <switch name="calculations/throttle1-pos-norm">
    <default value="fcs/throttle1-pos-norm"/>
    <test value="fcs/throttle-cmd-norm[0]">
     systems/engines/emerdisable_afterburning eq 1
    </test>
    <output>fcs/throttle-pos-norm[0]</output>
   </switch>
   <switch name="calculations/throttle2-pos-norm">
    <default value="fcs/throttle2-pos-norm"/>
    <test value="fcs/throttle-cmd-norm[1]">
     systems/engines/emerdisable_afterburning eq 1
    </test>
    <output>fcs/throttle-pos-norm[1]</output>
   </switch>

   </channel>

  <channel name="Pitch">
		
<!--
	  <summer>
			<input>fcs/elevator-pos-rad</input>
			<input>/systems/FCS/elevator-domain</input>
			<output>fcs/elevator-pos-rad</output>
	  </summer>
-->

   <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> -0.50 </min>
        <max>  0.50 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.50 </min>
        <max>  0.50 </max>
      </domain>
      <range>
        <min> -1 </min>
        <max>  1 </max>
      </range>
      <output>fcs/elevator-pos-norm</output>
   </aerosurface_scale>

  </channel>

  <channel name="Roll">

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

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

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

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

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

  </channel>

  <property value="1">fcs/yaw-damper-enable</property>
  <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>

   <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>
      <gain>fcs/yaw-damper-enable</gain>
   </scheduled_gain>

   <summer name="Rudder Sum">
      <input>fcs/rudder-command-sum</input>
      <input>fcs/yaw-damper-rate</input>
      <clipto>
        <min> -1.1 </min>
        <max>  1.1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-sum</input>
      <domain>
        <min> -1.1 </min>
        <max>  1.1 </max>
      </domain>
      <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>
  
<!--
Need testing :experimental brake parachute
-->
  <property>fcs/parachute_reef-cmd-norm</property>
  <property value="0">fcs/parachute/drop_cmd</property>

  <channel name="Drag Parachute">

   <kinematic name="Parachute Control">
     <input>fcs/parachute_reef-cmd-norm</input>
     <traverse>
       <setting>
          <position> 0 </position>
          <time>     0 </time>
       </setting>
       <setting>
          <position> 1 </position>
          <time>   0.9 </time>
       </setting>
     </traverse>
     <output>fcs/parachute_reef_pos</output>
   </kinematic>

   <switch name="systems/parachute/release_drop">
    <default value="fcs/parachute_reef_pos"/>
    <test logic="AND" value="0.0">
     fcs/parachute_reef_pos eq 1
     fcs/parachute/drop_cmd eq 1
    </test>
     <test logic="AND" value="0.0">
      fcs/parachute_reef_pos eq 1
      velocities/vc-fps gt 514.413823272
     </test>
    <output>fcs/parachute_reef_pos_norm</output>
   </switch>

  </channel>

 </flight_control>

 <aerodynamics>

  <axis name="LIFT">

    <function name="aero/force/Lift_alpha">
      <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>
            <!--Need of further testing -->
            <tableData>
              -0.200 -0.640
               0.000  0.120
               0.087  0.460
               0.260  1.120
               0.600  0.448
            </tableData>
<!--
            <tableData>
              -0.20 -0.640
               0.00  0.080
               0.26  1.000
               0.60  0.448
            </tableData>
-->
          </table>
      </product>
    </function>

    <function name="aero/force/Lift_flap">
       <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> 0.0200 </value>
       </product>
    </function>

    <function name="aero/force/Lift_speedbrake">
       <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/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>0.6</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>
<!--				These are the original values from Aeromatic(sill needs a bit of adjustement)
			<tableData>
             -1.57    1.500
             -0.26    0.031
              0.00    0.024
              0.26    0.031
              1.57    1.500
            </tableData>
-->
            <tableData>
             -1.57    0.840
             -0.26    0.016
              0.00    0.0067
              0.26    0.012
              1.57    0.640
            </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>0.1</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
                0.81      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> 0.00200 </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>0.01</value>
         </product>
    </function>

    <function name="aero/force/Drag_speedbrake">
       <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/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</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/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>
          <value>0.12</value>
       </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>0.01</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>-0.1</value>
       </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     -1.100
              2.0     -0.400
            </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>-23</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>-9</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>-0.15</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>

<external_reactions>
  <property>fcs/parachute_reef_pos_norm</property>
  <force name="parachute" frame="WIND">
    <function>
      <product>
        <p> aero/qbar-psf </p>
        <p> fcs/parachute_reef_pos_norm </p>
        <v> 1.0 </v> <!-- Full drag coefficient -->
        <v> 182.98 </v> <!-- Full parachute area -->
      </product>
    </function>
    <!-- The location below is in structural frame (x positive
         aft), so this location describes a point 1 foot aft
         of the origin. In this case, the origin is the center. -->
    <location unit="FT">
      <x>1</x>
      <y>0</y>
      <z>0</z>
    </location>
    <!-- The direction describes a unit vector. In this case, since
         the selected frame is the WIND frame, the "-1" x component
         describes a direction exactly opposite of the direction
         into the wind vector. That is, the direction specified below
         is the direction that the drag force acts in. -->
    <direction>
      <x>-1</x>
      <y> 0</y>
      <z> 1</z>
    </direction>
  </force>
</external_reactions>

</fdm_config>