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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<!-- Source: http://forum.flightgear.org/viewtopic.php?f=25&t=21664&start=45 -->
<fdm_config name="c182t" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Unknown, Dany93, HHS </author>
<filecreationdate> 2002-01-01 </filecreationdate>
<version> $Id: c172p.xml,v 1.40 June 2015 $ </version>
<!-- experimental stall and spin, up to flat spin March 2014 -->
<!-- Source: http://forum.flightgear.org/viewtopic.php?f=25&t=21664&start=45 -->
<!-- this file with comments for stall and spin to help -->
<!-- from further modifications for c172p-detailed 2015 -->
<!--many coefficients from David Megginson: http://www.megginson.com/Aviation/roskam-coefficients.html#sec.data-->
<description> Cessna C-182T </description>
</fileheader>
<metrics>
<wingarea unit="FT2"> 174 </wingarea>
<wingspan unit="FT"> 36 </wingspan>
<chord unit="FT"> 4.9 </chord>
<htailarea unit="FT2"> 21.9 </htailarea>
<htailarm unit="FT"> 17.7 </htailarm>
<vtailarea unit="FT2"> 16.5 </vtailarea>
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x>37.37 </x>
<y> 0 </y>
<z>32.94 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> -13 </x>
<y> 0 </y>
<z> 23.68 </z>
</location>
<location name="VRP" unit="IN"><!--Datum according POH -->
<x>-3.25</x>
<y> 0 </y>
<z>0 </z>
</location>
</metrics>
<mass_balance> <!--SLUG*FT2 from http://www.megginson.com/Aviation/roskam-coefficients.html#sec.data-->
<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"> 1925 </emptywt>
<location name="CG" unit="IN">
<x>40.37</x><!--according to POH-->
<y> 0 </y>
<z> 0 </z>
</location>
<pointmass name="Pilot">
<weight unit="LBS"> 180 </weight>
<location name="POINTMASS" unit="IN">
<x> 37 </x>
<y>-9.88</y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="Co-Pilot">
<weight unit="LBS"> 0 </weight> <!-- <weight unit="LBS">180</weight> -->
<location name="POINTMASS" unit="IN">
<x> 37 </x>
<y> 9.88 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="Left Passenger">
<weight unit="LBS"> 0 </weight> <!-- <weight unit="LBS">180</weight> -->
<location name="POINTMASS" unit="IN">
<x> 74 </x>
<y> -9.88 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="Right Passenger">
<weight unit="LBS"> 0 </weight> <!-- <weight unit="LBS">180</weight> -->
<location name="POINTMASS" unit="IN">
<x> 74 </x>
<y> 9.88 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="BaggageA">
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 97 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="BaggageB">
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 116 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x>-10.31 </x>
<y> 0 </y>
<z>-48.09</z><!--includes offset due to gear compression animation, should be -47.17-->
</location>
<static_friction> 0.99 </static_friction>
<dynamic_friction> 0.8 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT">3600 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">1800 </damping_coeff>
<max_steer unit="DEG"> 11 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x>54.43 </x>
<y>-51.56 </y>
<z>-44.67 </z><!--includes offset due to gear compression animation, should be -41.56-->
</location>
<static_friction> 0.99 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">400 </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>54.43 </x>
<y>51.56 </y>
<z>-44.67 </z><!--includes offset due to gear compression animation, should be -41.56-->
</location>
<static_friction> 0.99 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT">5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">400 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="TAIL_SKID">
<location unit="IN">
<x> 219.33 </x>
<y> 0 </y>
<z> 4.15 </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"> 2900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="LEFT_WINGTIP">
<location unit="IN">
<x>12.03 </x>
<y>-212.86 </y>
<z> 33.37 </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">2900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="RIGHT_WINGTIP">
<location unit="IN">
<x> 12.03 </x>
<y> 212.86 </y>
<z> 33.37 </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"> 2900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="NOSETIP">
<location unit="IN">
<x> -92.50 </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"> 2900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="ROOF_FRONT">
<location unit="IN">
<x> -4.82 </x>
<y> 0</y>
<z> 31.37 </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"> 2900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="ROOF_BACK">
<location unit="IN">
<x>58.47</x>
<y> 0</y>
<z>30.62 </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"> 2900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="HSTAB_TIP">
<location unit="IN">
<x> 214.47 </x>
<y> 0</y>
<z>79.41 </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"> 1900 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 540 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="engIO540AB1A5">
<location unit="IN">
<x>-40.94 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<thruster file="prop_79in3v">
<location unit="IN">
<x> -73.62 </x>
<y> 0 </y>
<z> 0</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 with 44 gallons =290.5lbs ?? kerosin but should be AVGas!-->
<location unit="IN">
<x>36.27 </x>
<y>-59.49 </y>
<z> 31.21</z>
</location>
<capacity unit="LBS"> 264.88 </capacity>
<contents unit="LBS"> 264.88</contents>
<density unit="LBS/GAL"> 6.02 </density>
<type> AVGAS</type>
</tank>
<tank type="FUEL"> <!-- Tank number 1 with 44 gallons =290.5lbs kerosin but should be AVGas!-->
<location unit="IN">
<x> 36.27 </x>
<y>59.49 </y>
<z> 31.21 </z>
</location>
<capacity unit="LBS"> 264.88 </capacity>
<contents unit="LBS"> 264.88 </contents>
<density unit="LBS/GAL"> 6.02 </density>
<type> AVGAS</type>
</tank>
</propulsion>
<flight_control name="FCS: c182s">
<!--Cessna 182S POH Page 7-12: nose gear steer deg=11deg, by applying left or right brake increasing steer deg up to 29deg-->
<channel name = "groundcontrol">
<fcs_function name="left brake nose-gear">
<function name="fcs/nose-gear-left-brake-steer-factor">
<product>
<property>fcs/left-brake-cmd-norm</property>
<value>-1</value>
</product>
</function>
</fcs_function>
<fcs_function name="right brake nose-gear">
<function name="fcs/nose-gear-right-brake-steer-factor">
<product>
<property>fcs/right-brake-cmd-norm</property>
<value>1</value>
</product>
</function>
</fcs_function>
<summer name="Brake-Sum">
<input>fcs/nose-gear-right-brake-steer-factor</input>
<input>fcs/nose-gear-left-brake-steer-factor</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<fcs_function name="Nose Wheel Steering">
<function name="fcs/brake-steer-influence">
<description>Steering command for nose gear</description>
<table>
<independentVar lookup="row">fcs/brake-sum</independentVar>
<independentVar lookup="column">fcs/steer-cmd-norm</independentVar>
<tableData>
-1 0 1
-1 -29 0 11
0 -11 0 11
1 -11 0 29
</tableData>
</table>
</function>
<output>fcs/steer-pos-deg</output>
</fcs_function>
</channel>
<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>21</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>21</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"><!-- Perpendicular to hinge line-->
<input>fcs/yaw-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-27</min>
<max>27</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder Position Normalized">
<input>fcs/rudder-pos-deg</input><!-- Perpendicular to hinge line-->
<domain>
<min>-27</min>
<max>27</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>0.26315</position>
<time>4</time>
</setting>
<setting>
<position>0.526315</position>
<time>4</time>
</setting>
<setting>
<position>1</position>
<time>4</time>
</setting>
</traverse>
<output>fcs/flap-pos-norm</output>
</kinematic>
<aerosurface_scale name="Flap Position Normalizer">
<input>fcs/flap-pos-norm</input>
<domain>
<min>0</min>
<max>1</max>
</domain>
<range>
<min>0</min>
<max>38</max>
</range>
<output>fcs/flap-pos-deg</output>
</aerosurface_scale>
<kinematic name="Flaps Lever">
<input>/controls/flight/flaps</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>1</time>
</setting>
</traverse>
<output>/sim/model/c182/cockpit/flaps-lever</output>
</kinematic>
</channel>
<!--
Cowl Flaps
-->
<channel name="Cowl Flaps">
<kinematic name="Cowl Flaps">
<input>/controls/engines/engine[0]/cowl-flaps-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>1</time>
</setting>
</traverse>
<output>propulsion/engine[0]/cowl-flaps-norm</output>
</kinematic>
<aerosurface_scale name="Left Cooling Factor">
<input>propulsion/engine[0]/cowl-flaps-norm</input>
<gain>1.0</gain>
<zero_centered>false</zero_centered>
<domain>
<min>0</min>
<max>1</max>
</domain>
<range>
<min>0.48</min>
<max>0.75</max>
</range>
<output>propulsion/engine[0]/cooling-factor</output>
</aerosurface_scale>
</channel>
<channel name= "brake-lever">
<kinematic name="brake-lever">
<input>/controls/gear/brake-parking</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>1</time>
</setting>
</traverse>
<output>/sim/model/c182/cockpit/brake-lever</output>
</kinematic>
</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>0.297</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>
<value>1.0</value>
</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>
<value>1.0</value>
</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>
</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="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>
0.00 1.00
-0.09 -0.22 -0.22
0.00 0.25 0.25
0.09 0.73 0.73
0.10 0.83 0.78
0.12 0.92 0.79
0.14 1.02 0.81
0.16 1.08 0.82
0.17 1.13 0.83
0.19 1.19 0.85
0.21 1.25 0.86
0.24 1.35 0.88
0.26 1.44 0.90
0.28 1.47 0.92
0.30 1.43 0.95
0.32 1.38 0.99
0.34 1.30 1.05
0.36 1.15 1.15
0.52 1.47 1.47
0.70 1.65 1.65
0.87 1.47 1.47
1.05 1.17 1.17
1.57 0.01 0.01
</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
38.0000 0.4445
</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>1.700</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>3.9</value>
</product>
</function>
</axis>
<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
38.0000 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 38.0000
-0.0873 0.0041 0.0000 0.0005 0.00178
-0.0698 0.0013 0.0004 0.0025 0.00521
-0.0524 0.0001 0.0023 0.0059 0.01064
-0.0349 0.0003 0.0057 0.0108 0.01791
-0.0175 0.0020 0.0105 0.0172 0.02692
0.0000 0.0052 0.0168 0.0251 0.03797
0.0175 0.0099 0.0248 0.0346 0.05105
0.0349 0.0162 0.0342 0.0457 0.06618
0.0524 0.0240 0.0452 0.0583 0.08319
0.0698 0.0334 0.0577 0.0724 0.10211
0.0873 0.0442 0.0718 0.0881 0.12294
0.1047 0.0566 0.0874 0.1053 0.14580
0.1222 0.0706 0.1045 0.1240 0.17056
0.1396 0.0860 0.1232 0.1442 0.19736
0.1571 0.0962 0.1353 0.1573 0.21463
0.1745 0.1069 0.1479 0.1708 0.23241
0.1920 0.1180 0.1610 0.1849 0.25083
0.2094 0.1298 0.1746 0.1995 0.27000
0.2269 0.1424 0.1892 0.2151 0.29032
0.2443 0.1565 0.2054 0.2323 0.31293
0.2618 0.1727 0.2240 0.2521 0.33871
0.2793 0.1782 0.2302 0.2587 0.34735
0.2967 0.1716 0.2227 0.2507 0.33693
0.3142 0.1618 0.2115 0.2388 0.32144
0.3316 0.1475 0.1951 0.2214 0.29858
0.3491 0.1097 0.1512 0.1744 0.23698
</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>0.1500</value>
</product>
</function>
<function name="aero/coefficient/CDcowl">
<description>Drag_due_to_cowl_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<property>propulsion/engine[0]/cowl-flaps-norm</property>
<value>0.0097</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>
<property>aero/beta-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.393
0.0943 -0.404
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYp">
<description>sideforce variation 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>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0750
0.0943 -0.1450
</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-rad_sec</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 0.201
0.0943 0.267
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYdr">
<description>Side_force_due_to_rudder</description>
<product>
<property>aero/function/qbar-induced-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.187</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>
<property>aero/beta-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0923
0.0943 -0.0895
</tableData>
</table>
<!--
stall and spin (1):
via diedra effect.
Makes the higher (downwind) wing drop at forward slip
and worsens the spin in a skidding turn.
But if too great, prevents the spin departure in a slipping turn
-->
<table>
<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
<tableData>
0.279 1
0.297 3.5
</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>
<table>
<independentVar lookup="row">velocities/p-aero-rad_sec</independentVar>
<tableData>
-20 20
-10 9.68
-5 2.42
0 0
5 -2.42
10 -9.68
20 -20
</tableData>
</table>
<!--
stall and spin (2):
less roll damping-->
<table>
<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
<tableData>
0.279 1
0.297 0.4
</tableData>
</table>
</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>aero/alpha-rad</independentVar>
<tableData>
0.0000 0.0798
0.0943 0.1869
</tableData>
</table>
<table>
<!--
stall and spin (3):
yaw effect
-->
<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
<independentVar lookup="column">velocities/r-aero-rad_sec</independentVar>
<independentVar lookup="table">aero/stall-hyst-norm</independentVar>
<tableData breakPoint="0">
-0.15 -0.1 0 0.1 0.15
0.279 1 1 1 1 1
0.297 35 30 1 30 35
0.5 5 5 1 5 5
</tableData>
<tableData breakPoint="1">
-0.15 -0.1 0 0.1 0.15
0.297 35 30 1 30 35
0.5 5 5 1 5 5
</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>
<!--
stall and spin (4):
less efficient ailerons
-->
<table>
<independentVar lookup="row">aero/alpha-wing-rad</independentVar>
<independentVar lookup="column">aero/stall-hyst-norm</independentVar>
<tableData>
0 1
0.279 1 0.3
0.297 0.3 0.3
0.611 -0.1 -0.1
</tableData>
</table>
</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>
<table>
<independentVar>velocities/u-aero-fps</independentVar>
<tableData>
107.1 0.090 <!--Approach-->
133.5 0.040 <!--climb-->
220.1 0.040<!--cruise-->
</tableData>
</table>
</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>-1.8</value>
<!--
stall and spin (5):
horizontal tail stall (for flat spin)
-->
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
20 1
25 0.6
35 0.4
45 0.5
55 0.4
65 0.2
90 0.1
</tableData>
</table>
</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>
<table>
<independentVar>velocities/u-aero-fps</independentVar>
<tableData>
107.1 -11.40 <!--Approach-->
133.5 -15.20 <!--climb-->
220.1 -12.40<!--cruise-->
</tableData>
</table>
</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>
<table>
<independentVar>velocities/u-aero-fps</independentVar>
<tableData>
107.1 -5.40 <!--Approach-->
133.5 -5.57 <!--climb-->
220.1 -7.27 <!--cruise-->
</tableData>
</table>
</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>
<table>
<independentVar>velocities/u-aero-fps</independentVar>
<tableData>
107.1 -1.029 <!--Approach-->
133.5 -1.369 <!--climb-->
220.1 -1.122 <!--cruise-->
</tableData>
</table>
<!--
stall and spin (6):
elevator loss of efficiency when stalled
-->
<table>
<independentVar lookup="row">aero/alpha-deg</independentVar>
<tableData>
18 1
25 0.25
35 0.1
45 0.1
55 0.1
65 0.1
90 0.1
</tableData>
</table>
</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
38.0000 -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>
<property>aero/beta-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 0.0587
0.0943 0.0907
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnp">
<description>yawing 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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0278
0.0943 -0.0649
</tableData>
</table>
</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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0937
0.0943 -0.1199
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnrf">
<description>Yaw_moment_due_to_flat_spin</description>
<!--
stall and spin (7):
Feedback loop on yaw rate for flat spin.
Accelerates the yaw rate when stalled, up to a self-maintained flat spin (like a dead leaf).
r-aero-rad_sec with non-zero coefficients mainly sets the max yawing rate, if attained.
The coefficients set the yaw moment, thus the speed too, and the flatness of the spin.
Too great coefficients give an divergent effect and a non-recoverable spin.
(tricky)
-->
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<table>
<independentVar lookup="row">velocities/r-aero-rad_sec</independentVar>
<independentVar lookup="column">aero/alpha-wing-rad</independentVar>
<tableData>
0.279 0.4
-15 0 0
-5 0 0
-3 0 -0.3
-1 0 0
0 0 0
1 0 0
3 0 0.3
5 0 0
15 0 0
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnda">
<description>Yaw_moment_due_to_aileron</description>
<!--
stall and spin (8):
adverse yaw: can induce a adverse turn and spin when stalled
-->
<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>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0216
0.0943 -0.0504
</tableData>
</table>
</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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.0645
0.0943 -0.0805
</tableData>
</table>
</product>
</function>
</axis>
</aerodynamics>
<external_reactions>
<!-- Tiedowns use body frame (x positive forward, y positive
right, z positive down).-->
<force name="tiedown-left" frame="BODY">
<location unit="M">
<x> 0.794</x>
<y>-2.473</y>
<z> 0.691</z>
</location>
<direction>
<x>0.0</x>
<y>0.0</y>
<z>1.0</z>
</direction>
</force>
<force name="tiedown-right" frame="BODY">
<location unit="M">
<x> 0.794</x>
<y> 2.473</y>
<z> 0.691</z>
</location>
<direction>
<x>0.0</x>
<y>0.0</y>
<z>1.0</z>
</direction>
</force>
<force name="tiedown-tail" frame="BODY">
<location unit="M">
<x> 5.601</x>
<y> 0.0000</y>
<z>0.115</z>
</location>
<direction>
<x>0.0</x>
<y>0.0</y>
<z>1.0</z>
</direction>
</force>
</external_reactions>
<system file="c182s-stallhorn"/>
<system file="propulsion"/>
<system file="indicated-airspeed"/>
<system file="c182s-ground-effects"/>
</fdm_config>
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