ATR72-500.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="ATR72-500" version="2.0" release="ALPHA"
   xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
   xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

 <fileheader>
  <author> Narendran Muraleedharan, thanks to Donald (igloocoder) and Oliver (ot-666)</author>
  <filecreationdate> 2012-07-08 </filecreationdate>
  <version>1.0</version>
  <description> ATR72-500 (Pratt and Whitney PW127F Engines) </description>
 </fileheader>

 <metrics>
   <wingarea  unit="FT2">  740 </wingarea> <!-- wingarea  unit="FT2">  656.60 </wingarea -->
   <wingspan  unit="FT" >   88.75 </wingspan>
   <wing_incidence>          2.00 </wing_incidence>
   <chord     unit="FT" >    8.63 </chord>
   <htailarea unit="FT2">  133.44 </htailarea>
   <htailarm  unit="FT" >   44.58 </htailarm>
   <vtailarea unit="FT2">  265.55 </vtailarea>
   <vtailarm  unit="FT" >   44.57 </vtailarm>
   <location name="AERORP" unit="IN">
     <x>   0.00 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="EYEPOINT" unit="IN">
     <x>   0.00 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   <location name="VRP" unit="IN">
     <x>0</x>
     <y>0</y>
     <z>0</z>
   </location>
 </metrics>

 <mass_balance>
   <ixx unit="SLUG*FT2">    232683 </ixx>
   <iyy unit="SLUG*FT2">    124973 </iyy>
   <izz unit="SLUG*FT2">    570228 </izz>
   <emptywt unit="LBS" >     28550 </emptywt>
   <location name="CG" unit="IN">
     <x>   -6.00 </x>
     <y>   0.00 </y>
     <z>   0.00 </z>
   </location>
   
   <pointmass name="Crew">
    <weight unit="LBS"> 380 </weight>
		<location name="POINTMASS" unit="IN">
		    <x> -415.27 </x>
		    <y> 0 </y>
		    <z> 40.97 </z>
		</location>
   </pointmass>
   <pointmass name="Cargo">
    <weight unit="LBS"> 750 </weight>
		<location name="POINTMASS" unit="IN">
		    <x> -240.12 </x>
		    <y> 0 </y>
		    <z> 11.82 </z>
		</location>
   </pointmass>
   <pointmass name="Passengers">
    <weight unit="LBS"> 13320 </weight>
		<location name="POINTMASS" unit="IN">
		    <x> 20.15 </x>
		    <y> 0 </y>
		    <z> 27.58 </z>
		</location>
   </pointmass>
 </mass_balance>

 <ground_reactions>

  <contact type="BOGEY" name="NOSE">
   <location unit="IN">
     <x> -441.67 </x>
     <y>   0.00 </y>
     <z> -61.464 </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">      15000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
   <max_steer unit="DEG"> 70 </max_steer>
   <brake_group>NONE</brake_group>
   <retractable>1</retractable>
</contact>

  <contact type="BOGEY" name="LEFT_MAIN">
   <location unit="IN">
     <x> 1.51 </x>
     <y> -76.83 </y>
     <z> -69.59 </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">      70000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 3500 </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> 1.51 </x>
     <y> 76.83 </y>
     <z> -69.59 </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">      70000 </spring_coeff>
   <damping_coeff unit="LBS/FT/SEC"> 3500 </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> -10.64 </x>
     <y> -527.56 </y>
     <z> 74.072 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      49604.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  9920.80 </damping_coeff>
 </contact>

  <contact type="STRUCTURE" name="RIGHT_WING">
    <location unit="IN">
     <x> -10.64 </x>
     <y> 527.56 </y>
     <z> 74.072 </z>
    </location>
    <static_friction>  0.80 </static_friction>
    <dynamic_friction> 0.50 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      49604.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  9920.80 </damping_coeff>
 </contact>
 
 <contact type="STRUCTURE" name="TAIL">
    <location unit="IN">
     <x> 392.424 </x>
     <y> 0 </y>
     <z> -5.516 </z>
    </location>
    <static_friction>  1.00 </static_friction>
    <dynamic_friction> 0.80 </dynamic_friction>
    <spring_coeff unit="LBS/FT">      49604.00 </spring_coeff>
    <damping_coeff unit="LBS/FT/SEC">  9920.80 </damping_coeff>
 </contact>

 </ground_reactions>

 <propulsion>

   <!-- engine file="pw127f" -->
   <engine file="nasalEngine">
    <location unit="IN">
      <x> -97.71 </x>
      <y> -159.18 </y>
      <z> 57.92 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>2</feed>
    <thruster file="prop_hs568f">
		<sense>1</sense>
		<p_factor>50</p_factor>
     <location unit="IN">
       <x> -151.26 </x>
      <y> -159.18 </y>
      <z> 57.92 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

   <!-- engine file="pw127f" -->
   <engine file="nasalEngine">
    <location unit="IN">
      <x> -97.71 </x>
      <y> 159.18 </y>
      <z> 57.92 </z>
    </location>
    <orient unit="DEG">
      <pitch> 0.00 </pitch>
      <roll>   0.00 </roll>
      <yaw>   0.00 </yaw>
    </orient>
    <feed>3</feed>
     <thruster file="prop_hs568f">
     	<sense>1</sense>
		<p_factor>50</p_factor>
     <location unit="IN">
      <x> -151.26 </x>
      <y> 159.18 </y>
      <z> 57.92 </z>
     </location>
     <orient unit="DEG">
       <pitch> 0.00 </pitch>
       <roll>   0.00 </roll>
       <yaw>   0.00 </yaw>
     </orient>
    </thruster>
  </engine>

  <tank type="FUEL"> <!-- Left Wing -->
     <location unit="IN">
       <x> -24.034 </x>
       <y>-227.732 </y>
       <z>   75.25 </z>
     </location>
     <capacity unit="LBS"> 5511 </capacity>
     <contents unit="LBS"> 3000 </contents>
	 <temperature>59</temperature>
  </tank>

  <tank type="FUEL"> <!-- Right Wing -->
     <location unit="IN">
       <x> -24.034 </x>
       <y> 227.732 </y>
       <z>   75.25 </z>
     </location>
     <capacity unit="LBS"> 5511 </capacity>
     <contents unit="LBS"> 3000 </contents>
	 <temperature>59</temperature>
  </tank>
  
  <tank type="FUEL"> <!-- Left Pipes -->
     <location unit="IN">
       <x> -24.034 </x>
       <y>-165.732 </y>
       <z>   75.25 </z>
     </location>
     <capacity unit="LBS"> 355 </capacity>
     <contents unit="LBS"> 0 </contents>
	 <temperature>65</temperature>
  </tank>
  
  <tank type="FUEL"> <!-- Right Pipes -->
     <location unit="IN">
       <x> -24.034 </x>
       <y>165.732 </y>
       <z>   75.25 </z>
     </location>
     <capacity unit="LBS"> 355 </capacity>
     <contents unit="LBS"> 0 </contents>
	 <temperature>65</temperature>
  </tank>

 </propulsion>
 
 <system file="fuel"/>

 <flight_control name="FCS: ATR72-500">

  <channel name="Pitch">
   <summer name="Pitch Trim Sum">
      <input>fcs/elevator-cmd-norm</input>
      <input>fcs/pitch-trim-cmd-norm</input>
      <clipto>
        <min> -1 </min>
        <max>  1 </max>
      </clipto>
   </summer>

   <aerosurface_scale name="Elevator Control">
      <input>fcs/pitch-trim-sum</input>
      <range>
        <min> -0.35 </min>
        <max>  0.35 </max>
      </range>
      <output>fcs/elevator-pos-rad</output>
   </aerosurface_scale>

   <aerosurface_scale name="elevator normalization">
      <input>fcs/elevator-pos-rad</input>
      <domain>
        <min> -0.35 </min>
        <max>  0.35 </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>

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

   <aerosurface_scale name="Rudder Control">
      <input>fcs/rudder-command-sum</input>
      <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> 35 </position>
          <time>      6 </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> 35 </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>     8 </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>
  
  <channel name="Tiller">
		
		<switch name="/controls/gear/tiller-disabled">
            <default value="0"/>
            <test logic="AND" value="1">
                /controls/gear/tiller-enabled == 0
            </test>
        </switch>
        
        <fcs_function name="Nose Wheel Steering 0">
          <function name="fcs/steer-nose-deg[0]">
            <description>Steering command for nose gear</description>
            <sum>
              <product>
                <table>
                   <independentVar lookup="row">/controls/gear/tiller-cmd-norm</independentVar>
                   <independentVar lookup="column">/controls/flight/rudder</independentVar>
                   <tableData>
                      -1   0   1
                  -1 -70 -70 -70
                   0  -7   0   7
                   1  70  70  70
                   </tableData>
                </table>
                <property>/controls/gear/tiller-enabled</property>
              </product>
              <product>
                <product>
                   <property>/controls/flight/rudder</property>
                   <value>70</value>
                </product>
                <property>/controls/gear/tiller-disabled</property>
              </product>
            </sum>
          </function>
        </fcs_function>
        
        <!-- simulate rotational friction -->
        <actuator name="Gear Nose Actuator">
          <input>fcs/steer-nose-deg[0]</input>
          <rate_limit>70</rate_limit>
          <output>fcs/steer-pos-deg[0]</output>
        </actuator>
        
  </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>
            <tableData>
              -0.20 -0.720
               0.00  0.380
               0.22  1.500
               0.60  0.764
            </tableData>
          </table>
      </product>
    </function -->
    
    
    <!-- Lift due to alpha using polar analysis data from XFLR5 (Wing Using RA 1843 Airfoil)-->
    <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-deg</independentVar>
            <tableData>
			  -30	-2.52
		          -20	-1.59
		          -19	-1.51
		          -18	-1.43
		      	  -17	-1.35
          		  -16	-1.26
			  -15	-1.18
			  -14	-1.10
			  -13	-1.01
			  -12	-1.92
			  -11	-1.84
			  -10	-1.75
			   -9	-1.66
			   -8	-1.52
			   -7	-1.30
			   -6	-1.21
			   -5	-1.12
			   -4	-1.03
			   -3	 0.06
			   -2	 0.16
			   -1	 0.25
				0	 0.34
				1	 0.43
				2	 0.52
				3	 0.61
				4	 0.70
				5	 0.79
				6	 0.87
				7	 0.96
				8	 1.05
				9	 1.13
			   10	 1.20
			   11	 1.30
			   12	 1.38
			   13	 1.47
			   14	 1.54
			   15	 1.57
			   16	 1.59
			   17	 1.60
			   18	 1.62
			   19	 1.51
			   20	 1.02
			   21	 0.85
			   22	 0.67
            </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> 0.045 </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>0.3</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    1.600
             -0.26    0.039
              0.00    0.029
              0.26    0.039
              1.57    1.600
            </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>0.041</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
                0.72      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> 0.00230 </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>0.03</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>0.025</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>
          <table>
            <independentVar lookup="row">velocities/mach</independentVar>
            <tableData>
              0.0    0.170
              2.0    0.057
            </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>0.01</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>-0.4</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     -1.000
              2.0     -0.250
            </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>-22</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>-8</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>-0.1</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>-0.01</value>
       </product>
    </function>

  </axis>

 </aerodynamics>
 
 <!-- Propeller Thrust is applied here -->
 
 <external_reactions>
 
		<force name="hs568f_prop0" frame="BODY">
			<location unit="IN">
			  <x> -151.26 </x>
			  <y> -159.18 </y>
			  <z> 57.92 </z>
			</location>
			<orient unit="DEG">
			  <pitch> 0.00 </pitch>
			  <roll>   0.00 </roll>
			  <yaw>   0.00 </yaw>
			</orient>
			<direction>
			 <x>1</x>
			 <y>0</y>
			 <z>0</z>
			</direction>
		</force>
		
		<force name="hs568f_prop1" frame="BODY">
			<location unit="IN">
			  <x> -151.26 </x>
			  <y> 159.18 </y>
			  <z> 57.92 </z>
			</location>
			<orient unit="DEG">
			  <pitch> 0.00 </pitch>
			  <roll>   0.00 </roll>
			  <yaw>   0.00 </yaw>
			</orient>
			<direction>
			 <x>1</x>
			 <y>0</y>
			 <z>0</z>
			</direction>
		</force>
		
	</external_reactions>

</fdm_config>