iar80-jsb.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="IAR_80" 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>2011-08-05</filecreationdate>
  <version>$Revison: $</version>
  <description> Models a IAR_80. </description>
 </fileheader>

<!--
  File:     IAR_80.xml
  Inputs:
    name:          IAR_80
    type:          WWII fighter, subsonic sport, aerobatic
    max weight:    4961.25 lb
    wing span:     34.51612 ft
    length:        29.43057 ft
    wing area:     183.005 sq-ft
    gear type:     taildragger
    retractable?:  yes
    # engines:     1
    engine type:   piston
    engine layout: forward fuselage
    yaw damper?    no

  Outputs:
    wing loading:  27.11 lb/sq-ft
    CL-alpha:      4.5 per radian
    CL-0:          0.17
    CL-max:        1.2
    CD-0:          0.02
    K:             0.045

 Ref 1 http://adamone.rchomepage.com/cg_calc.htm
 A  =2.04
 B  =1.0
 S  =0.2
 Y  =5.26
 AA =1.277
 BB =0.766
 SS =0.40
 YY =1.723
 D  =5.412

A=2.02
B=1.09
S=0.19
Y=5.11
AA=1.29
BB=.673
SS=.42
YY=1.63
D=5.35

-->

 <metrics>
   <wingarea  unit="FT2">  183.00 </wingarea>
   <wingspan  unit="FT" >   34.52 </wingspan>
   <wing_incidence unit="DEG"> 2.00 </wing_incidence>
   <chord     unit="FT" >   5.30 </chord>
   <htailarea unit="M2">    3.2   </htailarea> <!-- ref 1. -->
   <htailarm  unit="M" >    5.412 </htailarm>
   <vtailarea unit="FT2">   18.30 </vtailarea>
   <vtailarm  unit="FT" >   17.66 </vtailarm>
<!-- Measured geometric cord from model agrees with aeromatic. 2.375 -->
<!-- AeroRP and CG are based on ref 1 NP and CG for 10% static margin -->
   <location name="AERORP" unit="M">
     <x> 2.76</x>
     <y> 0.00 </y>
     <z>-0.195 </z>
   </location>
   <location name="EYEPOINT" unit="M">
     <x>  4.8 </x>
     <y>  0.0 </y>
     <z>  1.0 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>
<!-- Intertial tensor from YASim -->
 <mass_balance>
   <ixx unit="SLUG*FT2">      4400 </ixx>
   <iyy unit="SLUG*FT2">     12700 </iyy>
   <izz unit="SLUG*FT2">     17000 </izz>
   <emptywt unit="LBS" >      3565 </emptywt>
   <location name="CG" unit="M">
     <x> 2.7 </x>
     <y> 0.00 </y>
     <z> -0.04 </z>
   </location>
<!-- Warning: Adjust the -set file if altering the order of the point-masses-->
   <pointmass name="Pilot">
     <weight unit="LBS"> 200 </weight>
     <location name="POINTMASS" unit="M">
       <x> 4.79 </x>
       <y>   0 </y>
       <z>-0.32</z>
     </location>
   </pointmass>

   <pointmass name="Left_Ordnace">
     <weight unit="LBS"> 111 </weight>
     <location name="POINTMASS" unit="M">
       <x> 2.384 </x>
       <y>-2.35 </y>
       <z> 0.25</z>
     </location>
   </pointmass>

   <pointmass name="Right_Ordnace">
     <weight unit="LBS"> 111 </weight>
     <location name="POINTMASS" unit="M">
       <x> 2.384 </x>
       <y> 2.35 </y>
       <z> 0.25</z>
     </location>
   </pointmass>

 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="M">
     <x> 2.325 </x>
     <y>-1.645 </y>
     <z>-1.916 </z>
   </location>
   <orientation unit="DEG">
      <pitch> 1.50 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
   </orientation>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       4961.25 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   992.25 </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> 2.325 </x>
     <y> 1.645 </y>
     <z>-1.916 </z>
   </location>
   <orientation unit="DEG">
      <pitch> 1.50 </pitch>
      <roll>  0.00 </roll>
      <yaw>   0.00 </yaw>
   </orientation>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.50 </dynamic_friction>
   <rolling_friction> 0.02 </rolling_friction>
   <spring_coeff unit="LBS/FT">       4961.25 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   992.25 </damping_coeff>
   <max_steer unit="DEG">0</max_steer>
   <brake_group>RIGHT</brake_group>
   <retractable>1</retractable>
 </contact>

  <contact type="BOGEY" name="TAIL">
   <location unit="M">
     <x> 7.941 </x>
     <y> 0.00 </y>
     <z>-0.325 </z>
   </location>
   <static_friction>  0.80 </static_friction>
   <dynamic_friction> 0.60 </dynamic_friction>
   <rolling_friction> 0.60 </rolling_friction>
   <spring_coeff unit="LBS/FT">       2000.00 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC">   800.00 </damping_coeff>
   <max_steer unit="DEG"> 0.00 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>0</retractable>
 </contact>

  <contact type="STRUCTURE" name="NOSE"><!-- This contact needs to be n=3 for blade strike to work! -->
    <location unit="M">
     <x> 0.2 </x>
     <y> 0.0 </y>
     <z> -0.95 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4961.25 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   992.25 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="BELLY">
    <location unit="M">
     <x>  2.6 </x>
     <y>  0.0 </y>
     <z> -1.1 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4961.25 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   992.25 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="LEFT_WING">
    <location unit="M">
     <x> 2.6 </x>
     <y>-5.2 </y>
     <z>-0.1</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4961.25 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   992.25 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="M">
     <x> 2.6 </x>
     <y> 5.2 </y>
     <z>-0.1</z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">       4961.25 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">   992.25 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <engine file="eng_gr14k">
    <location unit="M">
      <x>  0.975 </x>
      <y>  0.00 </y>
      <z>  0.00 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>0</feed>
    <feed>1</feed>
    <thruster file="prop_vdm_9">
     <location unit="M">
       <x>  0.288 </x>
       <y>  0.00 </y>
       <z>  0.00 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
     <p_factor> 15. </p_factor>
     <sense>-1</sense>
    </thruster>
  </engine>

  <tank type="FUEL" number="0">
     <priority> 1 </priority>
     <density unit="LBS/GAL"> 6.03 </density>
     <location unit="M">
       <x> 3.057 </x>
       <y> 0.00  </y>
       <z> 0.489 </z>
     </location>
     <capacity unit="LBS"> 260.00 </capacity>
     <contents unit="LBS"> 250.00 </contents>
  </tank>

  <tank type="FUEL" number="1">
     <priority> 2 </priority>
     <density unit="LBS/GAL"> 6.03 </density>
     <location unit="M">
       <x> 2.644 </x>
       <y> 0.00 </y>
       <z> 0.164 </z>
     </location>
     <capacity unit="LBS"> 464.00 </capacity>
     <contents unit="LBS"> 440.00 </contents>
  </tank>

  <tank type="FUEL" number="2" name="Oil">
     <priority> 0 </priority>
     <density unit="LBS/GAL"> 7.177 </density>
     <capacity unit="LBS"> 131.00 </capacity>
     <contents unit="LBS"> 131.00 </contents>
     <location name="POINTMASS" unit="M">
       <x>2.054 </x>
       <y>0. </y>
       <z>0.258</z>
     </location>
   </tank>

 </propulsion>

 <flight_control name="FCS: IAR_80">

  <channel name="Pitch">

   <aerosurface_scale name="fcs/pitch-trim-pos-norm">
      <input>fcs/pitch-trim-cmd-norm</input>
      <range>
        <min> -0.5236 </min>
        <max>  0.436 </max>
      </range>
   </aerosurface_scale>

   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-pos-norm</input>
      <input>fcs/afcs-pitch-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> -0.5236 </min>
        <max>  0.436 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.5236 </min>
        <max>  0.436 </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>
      <input>fcs/afcs-roll-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> -0.4189 </min>
        <max>  0.4538</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> -0.4189 </min>
        <max>  0.4538 </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> -0.4189 </min>
        <max>  0.4538 </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> -0.4189 </min>
        <max>  0.4538 </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>
      <input>fcs/afcs-yaw-cmd-norm</input>
      <clipto>
        <min> -1.0 </min>
        <max>  1.0 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-command-sum</input>
      <range>
        <min> -0.436 </min>
        <max>  0.436 </max>
      </range>
      <output>fcs/rudder-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="rudder normalization">
      <input>-fcs/rudder-pos-rad</input>
      <domain>
        <min> -0.436 </min>
        <max>  0.436 </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>

  <property>fcs/cowl-flaps-cmd-norm</property>
  <channel name="Cowl Flaps">
   <kinematic name="fcs/cowl-flaps-pos-norm">
     <input>fcs/cowl-flaps-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>
<property> propulsion/engine/blade_damage</property>
  <channel name="Engine">
   <fcs_function name="fcs/propeller-pitch">
     <function>
      <sum>
       <product>
        <property>fcs/advance-pos-norm</property>
        <value>-25</value>
       </product>
       <value>47.5</value>
       <product>
         <property> propulsion/engine/blade_damage</property>
        <value>50</value>
       </product>
      </sum>
     </function>
     <output>propulsion/engine/blade-angle</output>
  </fcs_function>

   <fcs_function name="fcs/cowl-flap-cooling">
     <function>
      <sum>
       <product>
        <property>fcs/cowl-flaps-pos-norm</property>
        <value>0.2</value>
       </product>
       <value>0.25</value>
      </sum>
     </function>
     <output>propulsion/engine/cooling-factor</output>
  </fcs_function>


   <fcs_function name="propulsion/functions/oil-burn">
     <function>
        <property>propulsion/engine/oil-burn-pps</property>
     </function>
     <output> propulsion/tank[2]/external-flow-rate-pps </output>
  </fcs_function>

   <fcs_function name="propulsion/functions/fuel-press-norm">
     <function>
       <table>
         <independentVar lookup="row">propulsion/tank[1]/contents-lbs</independentVar>
         <tableData>
            2	0.65
           30	1.
         </tableData>
        </table>
    </function>
   </fcs_function>

   <fcs_function name="propulsion/functions/mixture-ctrl">
     <function>
        <product>
         <property>fcs/mixture-cmd-norm</property>
         <property>propulsion/functions/fuel-press-norm</property>
        </product>
      </function>
     <output> fcs/mixture-pos-norm </output>
  </fcs_function>

  </channel>

 </flight_control>

 <system file="afcs"/>
 <aerodynamics>
  <function name="aero/function/cos-alpha">
   <description>Cosine of alpha</description>
    <cos>
     <property>aero/alpha-rad</property>
    </cos>
  </function>

  <function name="aero/function/sin-alpha">
   <description>Sine of alpha</description>
    <sin>
     <property>aero/alpha-rad</property>
    </sin>
  </function>

  <function name="aero/function/cos-beta">
   <description>Cosine of beta</description>
    <cos>
     <property>aero/beta-rad</property>
    </cos>
  </function>

  <function name="aero/function/sin-beta">
   <description>Sine of beta</description>
    <sin>
     <property>aero/beta-rad</property>
    </sin>
  </function>

  <function name="aero/function/cos2-alpha">
   <description>Cosine Squared of alpha</description>
    <product>
     <property>aero/function/cos-alpha</property>
     <property>aero/function/cos-alpha</property>
    </product>
  </function>

  <function name="aero/function/scos2-alpha">
   <description>Signed Cosine Squared of alpha</description>
    <product>
     <abs><property>aero/function/cos-alpha</property></abs>
     <property>aero/function/cos-alpha</property>
    </product>
  </function>

 <function name="aero/function/velocity-induced-fps">
  <description> velocity including the propulsion induced velocity.</description>
  <sum>
    <property>velocities/u-aero-fps</property>
   <property>propulsion/engine/prop-induced-velocity_fps</property>
   <property>propulsion/engine/prop-induced-velocity_fps</property>
  </sum>
 </function>

 <function name="aero/function/qbar-induced-psf">
  <description> q bar including the propulsion induced velocity.</description>
  <product>
   <property>aero/function/velocity-induced-fps</property>
   <property>aero/function/velocity-induced-fps</property>
   <property>atmosphere/rho-slugs_ft3</property>
   <value>0.5</value>
  </product>
 </function>

  <function name="aero/function/ground-effect-factor-normal">
   <description>Change in normal due to ground effect factor</description>
   <product>
    <table>
     <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
     <independentVar lookup="column"><property>aero/function/sin-alpha</property></independentVar>
     <tableData>
             -1.0 0.000 1.0
        0.0   1.0 1.203 1.0
        0.1   1.0 1.127 1.0
        0.15  1.0 1.090 1.0
        0.2   1.0 1.073 1.0
        0.3   1.0 1.046 1.0
        0.4   1.0 1.055 1.0
        0.5   1.0 1.019 1.0
        0.6   1.0 1.013 1.0
        0.7   1.0 1.008 1.0
        0.8   1.0 1.006 1.0
        0.9   1.0 1.003 1.0
        1.0   1.0 1.002 1.0
        1.1   1.0 1.000 1.0
     </tableData>
    </table>
   </product>
  </function>

  <function name="aero/function/ground-effect-factor-axial">
   <description>Change in axial force due to ground effect</description>
   <product>
    <table>
     <independentVar lookup="row">aero/h_b-mac-ft</independentVar>
     <independentVar lookup="column"><property>aero/function/sin-alpha</property></independentVar>
     <tableData>
            -1.0 0.000 1.0
        0.0  1.0 0.480 1.0
        0.1  1.0 0.515 1.0
        0.15 1.0 0.629 1.0
        0.2  1.0 0.709 1.0
        0.3  1.0 0.815 1.0
        0.4  1.0 0.882 1.0
        0.5  1.0 0.928 1.0
        0.6  1.0 0.962 1.0
        0.7  1.0 0.988 1.0
        0.8  1.0 1.0   1.0
        0.9  1.0 1.0   1.0
        1.0  1.0 1.0   1.0
        1.1  1.0 1.0   1.0
     </tableData>
    </table>
   </product>
  </function>
  <axis name="NORMAL">

    <function name="aero/coefficient/CLalpha">
     <!-- -12 to 18 degrees from datcom, other range estimated -->
      <description>Normal_due_to_alpha</description>
      <product>
         <property>aero/function/ground-effect-factor-normal</property>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
	-3.142	0
	-2.356	-1
	-1.571	-1.414
	-0.785	-1
	-0.524	-0.7
	-0.209	-1.006
	-0.105	-0.423
	0.000	0.143
	0.105	0.726
	0.209	1.199
	0.236	1.272
	0.262	1.327
	0.288	1.252
	0.314	1.128
	0.524	0.7
	0.785	1
	1.571	1.414
	2.356	1
	3.142	0
            </tableData>
          </table>
      </product>
    </function>

    <function name="aero/coefficient/dCNflap">
<!-- DATCOM -->
       <description>Delta_Lift_due_to_flaps</description>
       <product>
           <property>aero/function/ground-effect-factor-normal</property>
           <property>aero/function/scos2-alpha</property>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <table>
             <independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
             <tableData>
               0.0     0.0
               0.26    0.205
               0.52    0.368
               0.79    0.416
             </tableData>
           </table>
       </product>
    </function>

    <function name="aero/coefficient/CNde">
<!-- Datcom and guess for mach -->
       <description>Lift_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/function/cos2-alpha</property>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/elevator-pos-rad</property>
           <value name="CNde"> 0.377</value>
           <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     1.000
              0.64    0.8
              1.0     0.250
            </tableData>
          </table>
       </product>
    </function>

  </axis>

 <axis name="AXIAL">

    <function name="aero/coefficient/CX0">
<!-- -12 to 18 degrees from datcom, other range estimated -->
       <description>Drag_at_zero_lift</description>
       <product>
          <property>aero/function/ground-effect-factor-axial</property>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <tableData>
	-3.142	-0.100
	-2.356	0.141
	-1.571	0.000
	-0.785	-0.141
	-0.524	0.206
	-0.209	-0.135
	-0.105	-0.018
	0.000	0.016
	0.105	-0.031
	0.209	-0.153
	0.236	-0.19
	0.262	-0.227
	0.288	-0.247
	0.314	-0.251
	0.524	0.256
	0.785	-0.212
	1.571	0.000
	2.356	0.141
	3.142	-0.100
            </tableData>
          </table>
       </product>
    </function>
<!--
    <function name="aero/coefficient/CXi">
       <description>Induced_drag</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/cl-squared</property>
           <value>0.045</value>
         </product>
    </function>
-->
    <function name="aero/coefficient/CXmach">
<!-- Aeromatic -->
       <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
                0.75      0.000
                1.10      0.023
                1.80      0.015
            </tableData>
          </table>
        </product>
    </function>

   <function name="aero/coefficient/CXflap">
<!-- Datcom, 6 degree alpha line -->
       <description>Drag_due_to_flaps</description>
         <product>
           <property>aero/function/ground-effect-factor-axial</property>
           <property>aero/function/scos2-alpha</property>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">fcs/elevator-pos-rad</independentVar>
            <tableData>
              0.0     0.0
              0.26    0.0143
              0.52    0.0302
              0.79    0.0358
            </tableData>
          </table>
         </product>
    </function>

    <function name="aero/coefficient/CXgear-left">
<!-- Aeromatic -->
       <description>Drag_due_to_gear</description>
         <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>gear/gear-pos-norm</property>
           <value>0.03</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>0.02</value>
         </product>
    </function>

<!--
    <function name="aero/coefficient/CXbeta">
       <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>
              -3.14  0.00
              -2.88  0.050
              -1.57    1.230
              -0.26    0.050
               0.00    0.000
               0.26    0.050
               1.57    1.230
               2.88  0.050
               3.14  0.0
            </tableData>
          </table>
       </product>
    </function>
-->
    <function name="aero/coefficient/CXde">
<!-- Guess -->
       <description>Drag_due_to_Elevator_Deflection</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/mag-elevator-pos-rad</property>
           <value>0.04</value>
       </product>
    </function>

  </axis>

  <axis name="SIDE">

    <function name="aero/coefficient/CYb">
<!-- Datcom -->
       <description>Side_force_due_to_beta</description>
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>aero/function/sin-beta</property>
           <value>-0.8</value>
       </product>
    </function>

    <function name="aero/coefficient/CYr">
<!-- guess -->
       <description>Side_force_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.</value>
       </product>
    </function>

    <function name="aero/coefficient/CYp">
<!-- guess -->
       <description>Side_force_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.</value>
       </product>
    </function>

    <function name="aero/coefficient/CYdr">
<!-- guess -->
       <description>Side_force_due_to_rudder</description>
       <product>
           <property>aero/function/cos-beta</property>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>0.008</value>
       </product>
    </function>

  </axis>

  <axis name="ROLL">

    <function name="aero/coefficient/Clb">
       <description>Roll_moment_due_to_beta</description>
<!-- DATCOM -->
       <product>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>aero/function/sin-beta</property>
           <value>-0.1</value>
       </product>
    </function>

    <function name="aero/coefficient/Clp">
       <description>Roll moment due to roll rate extended to work at zero velocity</description>
       <product>
        <value>-0.4</value> <!-- Clp -->
        <property>velocities/p-aero-rad_sec</property>
        <property>atmosphere/rho-slugs_ft3</property>
        <property>metrics/Sw-sqft</property>
        <property>metrics/bw-ft</property>
        <property>metrics/bw-ft</property> <!-- b^2 -->
        <value>0.0625</value> <!-- constant from function -->
        <pow>
         <sum>
          <product>
           <property>metrics/bw-ft</property>
           <property>metrics/bw-ft</property> <!-- b^2 -->
           <property>velocities/p-aero-rad_sec</property>
           <property>velocities/p-aero-rad_sec</property><!-- Omega^2 -->
          </product>
          <product>
           <property>velocities/u-aero-fps</property>
           <property>velocities/u-aero-fps</property>
           <value>16</value>
          </product>
         </sum>
         <value>0.5</value>
        </pow>
       </product>
    </function>

    <function name="aero/coefficient/Clr">
!-- Aeromatic -->
       <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>
<!-- Aeromatic -->
       <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    0.180
              2.0    0.060
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cldr">
       <description>Roll_moment_due_to_rudder</description>
<!-- Aeromatic -->
       <product>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value> 0.008</value>
       </product>
    </function>

  </axis>

  <axis name="PITCH">

    <function name="aero/coefficient/Cmalpha">
<!-- Aeromatic -->
       <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/function/sin-alpha</property>
           <value>-0.5</value>
       </product>
    </function>

    <function name="aero/coefficient/Cmde">
<!-- Datcom and guess for mach -->
       <description>Pitch_moment_due_to_elevator</description>
       <product>
          <property>aero/function/cos-alpha</property>
          <property>aero/function/qbar-induced-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <value name="Cmde"> -0.8</value>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0     1.000
              0.64    0.8
              1.0     0.250
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cmdf">
<!-- Datcom and guess for mach -->
       <description>Pitch_moment_due_to_flaps</description>
       <product>
          <property>aero/function/cos-alpha</property>
          <property>aero/function/qbar-induced-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <table>
            <independentVar lookup="row">fcs/flap-pos-rad</independentVar>
            <tableData>
              0.0     0.0
              0.26    0.0921
              0.52    0.1655
              0.79    0.1874
            </tableData>
          </table>
       </product>
    </function>

    <function name="aero/coefficient/Cmq">
<!-- Aeromatic -->
       <description>Pitch_moment_due_to_pitch_rate extended to work at zero velocity</description>
       <product>
        <value>-1.446</value> <!-- CMAD -->
        <property>velocities/q-aero-rad_sec</property>
        <property>atmosphere/rho-slugs_ft3</property>
        <property>metrics/Sw-sqft</property>
        <property>metrics/cbarw-ft</property>
        <property>metrics/cbarw-ft</property> <!-- b^2 -->
        <value>0.0625</value> <!-- constant from function -->
        <pow>
         <sum>
          <product>
           <property>metrics/cbarw-ft</property>
           <property>metrics/cbarw-ft</property> <!-- b^2 -->
           <property>velocities/q-aero-rad_sec</property>
           <property>velocities/q-aero-rad_sec</property><!-- Omega^2 -->
          </product>
          <product>
           <property>velocities/u-aero-fps</property>
           <property>velocities/u-aero-fps</property>
           <value>16</value>
          </product>
         </sum>
         <value>0.5</value>
        </pow>
       </product>
      </function>

    <function name="aero/coefficient/Cmadot">
<!-- Aeromatic -->
       <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>-7</value>
       </product>
    </function>

  </axis>

  <axis name="YAW">

    <function name="aero/coefficient/Cnb">
<!-- DATCOM -->
       <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/function/sin-beta</property>
           <value>0.12</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnr">
<!-- Aeromatic -->
       <description>Yaw_moment_due_to_yaw_rate extended to work at zero velocity</description>
       <product>
        <value>-0.1411</value> <!-- CNR -->
        <property>velocities/r-aero-rad_sec</property>
        <property>atmosphere/rho-slugs_ft3</property>
        <property>metrics/Sw-sqft</property>
        <property>metrics/bw-ft</property>
        <property>metrics/bw-ft</property> <!-- b^2 -->
        <value>0.0625</value> <!-- constant from function -->
        <pow>
         <sum>
          <product>
           <property>metrics/bw-ft</property>
           <property>metrics/bw-ft</property> <!-- b^2 -->
           <property>velocities/r-aero-rad_sec</property>
           <property>velocities/r-aero-rad_sec</property><!-- Omega^2 -->
          </product>
          <product>
           <property>velocities/u-aero-fps</property>
           <property>velocities/u-aero-fps</property>
           <value>16</value>
          </product>
         </sum>
         <value>0.5</value>
        </pow>
       </product>
    </function>


    <function name="aero/coefficient/Cnp">
<!-- Aeromatic -->
       <description>Yaw_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> 0.018</value>
       </product>
    </function>

    <function name="aero/coefficient/Cndr">
<!-- Aeromatic -->
       <description>Yaw_moment_due_to_rudder</description>
       <product>
           <property>aero/function/cos-alpha</property>
           <property>aero/function/qbar-induced-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/rudder-pos-rad</property>
           <value>-0.008</value>
       </product>
    </function>

    <function name="aero/coefficient/Cnda">
<!-- Aeromatic -->
       <description>Adverse_yaw</description>
       <product>
           <property>aero/function/cos-alpha</property>
           <property>aero/qbar-psf</property>
           <property>metrics/Sw-sqft</property>
           <property>metrics/bw-ft</property>
           <property>fcs/left-aileron-pos-rad</property>
           <value>-0.003</value>
       </product>
    </function>

  </axis>

 </aerodynamics>

</fdm_config>