Turbo-c170.xml

<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="Turbo-c170" version="1.0" release="ALPHA"
	    xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
	    xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">

  <fileheader>
    <author> Unknown </author>
    <filecreationdate> 2002-01-01 </filecreationdate>
    <description> Cessna Turbo-C-170 </description>
    <version> $Id: Turbo-c170.xml,v 1.0 2015/03/29 $ </version>
  </fileheader>

  <metrics>
    <wingarea unit="FT2"> 174 </wingarea>
    <wingspan unit="FT"> 35.8 </wingspan>
    <chord unit="FT"> 4.9 </chord>
    <htailarea unit="FT2"> 21.9 </htailarea>
    <htailarm unit="FT"> 15.7 </htailarm>
    <vtailarea unit="FT2"> 16.5 </vtailarea>
    <vtailarm unit="FT"> 0 </vtailarm>
    <location name="AERORP" unit="IN">
      <x> 43.2 </x>
      <y> 0 </y>
      <z> 59.4 </z>
    </location>
    <location name="EYEPOINT" unit="IN">
      <x> 37 </x>
      <y> 0 </y>
      <z> 48 </z>
    </location>
    <location name="VRP" unit="IN">
      <x> 42.6 </x>
      <y> 0 </y>
      <z> 38.5 </z>
    </location>
  </metrics>

  <mass_balance>
    <ixx unit="SLUG*FT2"> 948 </ixx>
    <iyy unit="SLUG*FT2"> 1346 </iyy>
    <izz unit="SLUG*FT2"> 1967 </izz>
    <ixy unit="SLUG*FT2"> -0 </ixy>
    <ixz unit="SLUG*FT2"> -0 </ixz>
    <iyz unit="SLUG*FT2"> -0 </iyz>
    <emptywt unit="LBS"> 1500 </emptywt>
    <location name="CG" unit="IN">
      <x> 41 </x>
      <y> 0 </y>
      <z> 36.5 </z>
    </location>
    <pointmass name="Pilot">
      <weight unit="LBS"> 180 </weight>
      <location name="POINTMASS" unit="IN">
        <x> 36 </x>
        <y> -14 </y>
        <z> 24 </z>
      </location>
    </pointmass>
    <pointmass name="Co-Pilot">
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
        <x> 36 </x>
        <y> 14 </y>
        <z> 24 </z>
      </location>
    </pointmass>
    <pointmass name="Left Passenger">
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
        <x> 70 </x>
        <y> -14 </y>
        <z> 24 </z>
      </location>
    </pointmass>
    <pointmass name="Right Passenger">
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
        <x> 70 </x>
        <y> 14 </y>
        <z> 24 </z>
      </location>
    </pointmass>
    <pointmass name="Baggage">
      <weight unit="LBS"> 0 </weight>
      <location name="POINTMASS" unit="IN">
        <x> 95 </x>
        <y>  0 </y>
        <z> 24 </z>
      </location>
    </pointmass>
  </mass_balance>

  <ground_reactions>
    <contact type="BOGEY" name="NOSE">
      <location unit="IN">
        <x> -6.8 </x>
        <y> 0 </y>
        <z> 0</z>
      </location>
      <static_friction> 0.2 </static_friction>
      <dynamic_friction> 0.2 </dynamic_friction>
      <rolling_friction> 0.2 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 1000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
      <max_steer unit="DEG"> 0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="BOGEY" name="LEFT_MAIN">
      <location unit="IN">
        <x> -1 </x>
        <y> -43 </y>
        <z> -30 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> LEFT </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="BOGEY" name="RIGHT_MAIN">
      <location unit="IN">
        <x> -1 </x>
        <y> 43 </y>
        <z> -30 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> RIGHT </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="BOGEY" name="TAIL_WHEEL">
      <location unit="IN">
        <x> 188 </x>
        <y> 0 </y>
        <z> -1 </z>
      </location>
      <static_friction> 0.8 </static_friction>
      <dynamic_friction> 0.5 </dynamic_friction>
      <rolling_friction> 0.02 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 1800 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
      <max_steer unit="DEG"> -10 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="BOGEY" name="LEFT_TIP">
      <location unit="IN">
        <x> 43.2 </x>
        <y> -214.8 </y>
        <z> 59.4 </z>
      </location>
      <static_friction> 0.2 </static_friction>
      <dynamic_friction> 0.2 </dynamic_friction>
      <rolling_friction> 0.2 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
    <contact type="BOGEY" name="RIGHT_TIP">
      <location unit="IN">
        <x> 43.2 </x>
        <y> 214.8 </y>
        <z> 59.4 </z>
      </location>
      <static_friction> 0.2 </static_friction>
      <dynamic_friction> 0.2 </dynamic_friction>
      <rolling_friction> 0.2 </rolling_friction>
      <spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
      <damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
      <max_steer unit="DEG"> 0.0 </max_steer>
      <brake_group> NONE </brake_group>
      <retractable>0</retractable>
    </contact>
  </ground_reactions>
  <propulsion>
    <engine file="engtm601mod">
      <location unit="IN">
        <x> -19.7 </x>
        <y> 0 </y>
        <z> 26.6 </z>
      </location>
      <orient unit="DEG">
        <roll> 0.0 </roll>
        <pitch> 0 </pitch>
        <yaw> 0 </yaw>
      </orient>
      <feed>0</feed>
      <feed>1</feed>
      <thruster file="dh-rotol90-4">
        <location unit="IN">
          <x> -37.7 </x>
          <y> 0 </y>
          <z> 26.6 </z>
        </location>
        <orient unit="DEG">
          <roll> 0.0 </roll>
          <pitch> 0.0 </pitch>
          <yaw> 0.0 </yaw>
        </orient>
        <sense> 1 </sense>
        <p_factor> 5 </p_factor>
      </thruster>
    </engine>
    <tank type="FUEL">    <!-- Tank number 0 -->
    <location unit="IN">
      <x> 56 </x>
      <y> -112 </y>
      <z> 59.4 </z>
    </location>
    <capacity unit="LBS"> 185 </capacity>
    <contents unit="LBS"> 100 </contents>
    </tank>
    <tank type="FUEL">    <!-- Tank number 1 -->
    <location unit="IN">
      <x> 56 </x>
      <y> 112 </y>
      <z> 59.4 </z>
    </location>
    <capacity unit="LBS"> 185 </capacity>
    <contents unit="LBS"> 100 </contents>
    </tank>
  </propulsion>
  <flight_control name="FCS: Turbo-c170">
    <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>
        <gain>0.01745</gain>
        <range>
          <min>-28</min>
          <max>23</max>
        </range>
        <output>fcs/elevator-pos-rad</output>
      </aerosurface_scale>

      <aerosurface_scale name="Elevator Position Normalized">
        <input>fcs/elevator-pos-deg</input>
        <domain>
          <min>-28</min>
          <max>23</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>
        <gain>0.01745</gain>
        <range>
          <min>-20</min>
          <max>15</max>
        </range>
        <output>fcs/left-aileron-pos-rad</output>
      </aerosurface_scale>

      <aerosurface_scale name="Left Aileron Position Normalized">
        <input>fcs/left-aileron-pos-deg</input>
        <domain>
          <min>-20</min>
          <max>15</max>
        </domain>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/left-aileron-pos-norm</output>
      </aerosurface_scale>

      <aerosurface_scale name="Right Aileron Control">
        <input>fcs/roll-trim-sum</input>
        <gain>-0.01745</gain>
        <range>
          <min>-20</min>
          <max>15</max>
        </range>
        <output>fcs/right-aileron-pos-rad</output>
      </aerosurface_scale>

      <aerosurface_scale name="Right Aileron Position Normalized">
        <input>fcs/right-aileron-pos-deg</input>
        <domain>
          <min>-15</min>
          <max>20</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="Yaw Trim Sum">
        <input>fcs/rudder-cmd-norm</input>
        <input>fcs/yaw-trim-cmd-norm</input>
        <clipto>
          <min>-1</min>
          <max>1</max>
        </clipto>
      </summer>

      <aerosurface_scale name="Rudder Control">
        <input>fcs/yaw-trim-sum</input>
        <gain>0.01745</gain>
        <range>
          <min>-16</min>
          <max>16</max>
        </range>
        <output>fcs/rudder-pos-rad</output>
      </aerosurface_scale>

      <aerosurface_scale name="Rudder Position Normalized">
        <input>fcs/rudder-pos-deg</input>
        <domain>
          <min>-16</min>
          <max>16</max>
        </domain>
        <range>
          <min>-1</min>
          <max>1</max>
        </range>
        <output>fcs/rudder-pos-norm</output>
      </aerosurface_scale>
    </channel>
    <channel name="Flaps">
      <kinematic name="Flaps Control">
        <input>fcs/flap-cmd-norm</input>
        <traverse>
          <setting>
            <position>0</position>
            <time>0</time>
          </setting>
          <setting>
            <position>10</position>
            <time>2</time>
          </setting>
          <setting>
            <position>20</position>
            <time>1</time>
          </setting>
          <setting>
            <position>30</position>
            <time>1</time>
          </setting>
        </traverse>
        <output>fcs/flap-pos-deg</output>
      </kinematic>
      <aerosurface_scale name="Flap Position Normalizer">
        <input>fcs/flap-pos-deg</input>
        <domain>
          <min>0</min>  <!-- Flaps actual minimum position -->
          <max>30</max>  <!-- Flaps actual maximum position -->
        </domain>
        <range>
          <min>0</min>  <!-- Flaps normalized minimum position -->
          <max>1</max>  <!-- Flaps normalized maximum position -->
        </range>
        <output>fcs/flap-pos-norm</output>
      </aerosurface_scale>
    </channel>
  </flight_control>
  <aerodynamics>

    <alphalimits unit="RAD">
      <min>-0.087</min>
      <max>0.28</max>
    </alphalimits>

    <hysteresis_limits unit="RAD">
      <min>0.09</min>
      <max>0.36</max>
    </hysteresis_limits>

    <function name="aero/function/kCDge">
      <description>Change_in_drag_due_to_ground_effect</description>
      <product>
        <table>
          <independentVar>aero/h_b-mac-ft</independentVar>
          <tableData>
            0.0000	0.4800
            0.1000	0.5150
            0.1500	0.6290
            0.2000	0.7090
            0.3000	0.8150
            0.4000	0.8820
            0.5000	0.9280
            0.6000	0.9620
            0.7000	0.9880
            0.8000	1.0000
            0.9000	1.0000
            1.0000	1.0000
            1.1000	1.0000
          </tableData>
        </table>
      </product>
    </function>

    <function name="aero/function/kCLge">
      <description>Change_in_lift_due_to_ground_effect</description>
      <product>
        <table>
          <independentVar>aero/h_b-mac-ft</independentVar>
          <tableData>
            0.0000	1.2030
            0.1000	1.1270
            0.1500	1.0900
            0.2000	1.0730
            0.3000	1.0460
            0.4000	1.0550
            0.5000	1.0190
            0.6000	1.0130
            0.7000	1.0080
            0.8000	1.0060
            0.9000	1.0030
            1.0000	1.0020
            1.1000	1.0000
          </tableData>
        </table>
      </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> 

    <axis name="DRAG">
      <function name="aero/coefficient/CDo">
        <description>Drag_at_zero_lift</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <value>0.027</value>
        </product>
      </function>
      <function name="aero/coefficient/CDDf">
        <description>Delta_drag_due_to_flap_deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCDge</property>
          <table>
            <independentVar>fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	0.0000
              10.0000	0.0070
              20.0000	0.0120
              30.0000	0.0180
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CDwbh">
        <description>Drag_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCDge</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	10.0000	20.0000	30.0000
              -0.0873	0.0041	0.0000	0.0005	0.0014
              -0.0698	0.0013	0.0004	0.0025	0.0041
              -0.0524	0.0001	0.0023	0.0059	0.0084
              -0.0349	0.0003	0.0057	0.0108	0.0141
              -0.0175	0.0020	0.0105	0.0172	0.0212
              0.0000	0.0052	0.0168	0.0251	0.0299
              0.0175	0.0099	0.0248	0.0346	0.0402
              0.0349	0.0162	0.0342	0.0457	0.0521
              0.0524	0.0240	0.0452	0.0583	0.0655
              0.0698	0.0334	0.0577	0.0724	0.0804
              0.0873	0.0442	0.0718	0.0881	0.0968
              0.1047	0.0566	0.0874	0.1053	0.1148
              0.1222	0.0706	0.1045	0.1240	0.1343
              0.1396	0.0860	0.1232	0.1442	0.1554
              0.1571	0.0962	0.1353	0.1573	0.1690
              0.1745	0.1069	0.1479	0.1708	0.1830
              0.1920	0.1180	0.1610	0.1849	0.1975
              0.2094	0.1298	0.1746	0.1995	0.2126
              0.2269	0.1424	0.1892	0.2151	0.2286
              0.2443	0.1565	0.2054	0.2323	0.2464
              0.2618	0.1727	0.2240	0.2521	0.2667
              0.2793	0.1782	0.2302	0.2587	0.2735
              0.2967	0.1716	0.2227	0.2507	0.2653
              0.3142	0.1618	0.2115	0.2388	0.2531
              0.3316	0.1475	0.1951	0.2214	0.2351
              0.3491	0.1097	0.1512	0.1744	0.1866
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CDDe">
        <description>Drag_due_to_Elevator_Deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/mag-elevator-pos-rad</property>
          <value>0.0000</value>
        </product>
      </function>
      <function name="aero/coefficient/CDbeta">
        <description>Drag_due_to_sideslip</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/mag-beta-rad</property>
          <value>0.1700</value>
        </product>
      </function>
    </axis>

    <axis name="SIDE">
      <function name="aero/coefficient/CYb">
        <description>Side_force_due_to_beta</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <table>
            <independentVar lookup="row">aero/beta-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	30.0000
              -0.3490	0.1370	0.1060
              0.0000	0.0000	0.0000
              0.3490	-0.1370	-0.1060
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CYda">
        <description>Side_force_due_to_aileron</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <value>0.0000</value>
        </product>
      </function>
      <function name="aero/coefficient/CYdr">
        <description>Side_force_due_to_rudder</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/rudder-pos-rad</property>
          <value>0.1870</value>
        </product>
      </function>
      <function name="aero/coefficient/CYp">
        <description>Side_force_due_to_roll_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/bi2vel</property>
          <property>velocities/p-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	30.0000
              0.0000	-0.0750	-0.1610
              0.0940	-0.1450	-0.2310
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CYr">
        <description>Side_force_due_to_yaw_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	30.0000
              0.0000	0.2140	0.1620
              0.0940	0.2670	0.2150
            </tableData>
          </table>
        </product>
      </function>
    </axis>

    <axis name="LIFT">
      <function name="aero/coefficient/CLwbh">
        <description>Lift_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">aero/stall-hyst-norm</independentVar>
            <tableData>
              0.0000	1.0000
              -0.0900	-0.2200	-0.2200
              0.0000	0.2500	0.2500
              0.0900	0.7300	0.7300
              0.1000	0.8300	0.7800
              0.1200	0.9200	0.7900
              0.1400	1.0200	0.8100
              0.1600	1.0800	0.8200
              0.1700	1.1300	0.8300
              0.1900	1.1900	0.8500
              0.2100	1.2500	0.8600
              0.2400	1.3500	0.8800
              0.2600	1.4400	0.9000
              0.2800	1.4700	0.9200
              0.3000	1.4300	0.9500
              0.3200	1.3800	0.9900
              0.3400	1.3000	1.0500
              0.3600	1.1500	1.1500
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CLDf">
        <description>Delta_lift_due_to_flap_deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/function/kCLge</property>
          <table>
            <independentVar>fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	0.0000
              10.0000	0.2000
              20.0000	0.3000
              30.0000	0.3500
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/CLDe">
        <description>Lift_due_to_Elevator_Deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>fcs/elevator-pos-rad</property>
          <value>0.4300</value>
        </product>
      </function>
      <function name="aero/coefficient/CLadot">
        <description>Lift_due_to_alpha_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>aero/alphadot-rad_sec</property>
          <property>aero/ci2vel</property>
          <value>1.7000</value>
        </product>
      </function>
      <function name="aero/coefficient/CLq">
        <description>Lift_due_to_pitch_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>velocities/q-aero-rad_sec</property>
          <property>aero/ci2vel</property>
          <value>3.9000</value>
        </product>
      </function>
    </axis>

    <axis name="ROLL">
      <function name="aero/coefficient/Clb">
        <description>Roll_moment_due_to_beta</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <table>
            <independentVar>aero/beta-rad</independentVar>
            <tableData>
              -0.3490	0.0322
              0.0000	0.0000
              0.3490	-0.0322
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/Clp">
        <description>Roll_moment_due_to_roll_rate_(roll_damping)</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>-0.4840</value>
        </product>
      </function>
      <function name="aero/coefficient/Clr">
        <description>Roll_moment_due_to_yaw_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <table>
            <independentVar lookup="row">aero/alpha-rad</independentVar>
            <independentVar lookup="column">fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	30.0000
              0.0000	0.0798	0.1246
              0.0940	0.1869	0.2317
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/ClDa">
        <description>Roll_moment_due_to_aileron</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/left-aileron-pos-rad</property>
          <value>0.2290</value>
        </product>
      </function>
      <function name="aero/coefficient/Cldr">
        <description>Roll_moment_due_to_rudder</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>fcs/rudder-pos-rad</property>
          <value>0.0147</value>
        </product>
      </function>
    </axis>

    <axis name="PITCH">
      <function name="aero/coefficient/Cmo">
        <description>Pitching_moment_at_zero_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <value>0.1000</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmalpha">
        <description>Pitch_moment_due_to_alpha</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <sin>
            <property>aero/alpha-rad</property>
          </sin>
          <value>-1.8000</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmq">
        <description>Pitch_moment_due_to_pitch_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/ci2vel</property>
          <property>velocities/q-aero-rad_sec</property>
          <value>-12.4000</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmadot">
        <description>Pitch_moment_due_to_alpha_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>aero/ci2vel</property>
          <property>aero/alphadot-rad_sec</property>
          <value>-7.2700</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmde">
        <description>Pitch_moment_due_to_elevator_deflection</description>
        <product>
          <property>aero/function/qbar-induced-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <property>fcs/elevator-pos-rad</property>
          <value>-1.1220</value>
        </product>
      </function>
      <function name="aero/coefficient/Cmdf">
        <description>Delta_pitching_moment_due_to_flap_deflection</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/cbarw-ft</property>
          <table>
            <independentVar>fcs/flap-pos-deg</independentVar>
            <tableData>
              0.0000	0.0000
              10.0000	-0.0654
              20.0000	-0.0981
              30.0000	-0.1140
            </tableData>
          </table>
        </product>
      </function>
    </axis>

    <axis name="YAW">
      <function name="aero/coefficient/Cnb">
        <description>Yaw_moment_due_to_beta</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <table>
            <independentVar>aero/beta-rad</independentVar>
            <tableData>
              -0.3490	-0.0205
              0.0000	0.0000
              0.3490	0.0205
            </tableData>
          </table>
        </product>
      </function>
      <function name="aero/coefficient/Cnp">
        <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>-0.0278</value>
        </product>
      </function>
      <function name="aero/coefficient/Cnr">
        <description>Yaw_moment_due_to_yaw_rate</description>
        <product>
          <property>aero/qbar-psf</property>
          <property>metrics/Sw-sqft</property>
          <property>metrics/bw-ft</property>
          <property>aero/bi2vel</property>
          <property>velocities/r-aero-rad_sec</property>
          <value>-0.0937</value>
        </product>
      </function>
      <function name="aero/coefficient/Cnda">
        <description>Yaw_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>-0.0053</value>
        </product>
      </function>
      <function name="aero/coefficient/Cndr">
        <description>Yaw_moment_due_to_rudder</description>
        <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>-0.0430</value>
        </product>
      </function>
    </axis>
  </aerodynamics>
  <!--
  <output name="JSBout172C.csv" type="CSV" rate="60">
    <property> aero/qbar-psf </property>
    <property> accelerations/udot-ft_sec2 </property>
    <property> accelerations/vdot-ft_sec2 </property>
    <property> accelerations/wdot-ft_sec2 </property>
    <property> accelerations/a-pilot-x-ft_sec2 </property>
    <property> accelerations/a-pilot-y-ft_sec2 </property>
    <property> accelerations/a-pilot-z-ft_sec2 </property>
    <property> accelerations/n-pilot-x-norm    </property>
    <property> accelerations/n-pilot-y-norm    </property>
    <property> accelerations/n-pilot-z-norm    </property>
    <rates> ON </rates>
    <velocities> ON </velocities>
    <forces> ON </forces>
    <moments> ON </moments>
    <position> ON </position>
    <fcs> OFF </fcs>
    <propulsion> OFF </propulsion>
    <aerosurfaces> OFF </aerosurfaces>
    <fcs> OFF </fcs>
    <ground_reactions> OFF </ground_reactions>
  </output>
  -->
</fdm_config>