forked from HHS81/c182s
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c182s.xml
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c182s.xml
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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="c182st" 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-182S </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">17.7 </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>
<pointmass name="Ice">
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x>37.37 </x>
<y> 0 </y>
<z>32.94 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x>-10.31 </x>
<y> 0 </y>
<z>-47.09</z><!--includes offset due to gear compression animation, should be -47.17-->
</location>
<static_friction> 0.5 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT">3600 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">900 </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>-43.67 </z><!--includes offset due to gear compression animation, should be -41.56-->
</location>
<static_friction> 0.5 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC">200 </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>-43.67 </z><!--includes offset due to gear compression animation, should be -41.56-->
</location>
<static_friction> 0.5</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">200 </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>5</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>
<!-- 0: left wing -->
<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>
<drain_location unit="M">
<x> 1.057 </x>
<y>-1.11821 </y>
<z> 0.68779 </z>
</drain_location>
<capacity unit="LBS"> 264.88 </capacity>
<contents unit="LBS"> 264.88</contents>
<temperature>50</temperature>
<density unit="LBS/GAL"> 6.02 </density>
<standpipe>2</standpipe>
<type>AVGAS</type>
</tank>
<!-- 1: right wing -->
<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>
<drain_location unit="M">
<x> 1.057 </x>
<y> 1.11821 </y>
<z> 0.68779 </z>
</drain_location>
<capacity unit="LBS"> 264.88 </capacity>
<contents unit="LBS"> 264.88 </contents>
<temperature>50</temperature>
<density unit="LBS/GAL"> 6.02 </density>
<standpipe>2</standpipe>
<type>AVGAS</type>
</tank>
<!-- 2: Fuel selector sump -->
<tank type="FUEL">
<location unit="IN">
<x>0.45</x>
<y>0</y>
<z>-0.40</z>
</location>
<drain_location unit="M">
<x>0.45</x>
<y>0</y>
<z>-0.45</z>
</drain_location>
<capacity unit="LBS">0.1</capacity> <!-- todo: arbitrary numer as i dont know exact ones -->
<contents unit="LBS">0</contents>
<temperature>50</temperature>
<density unit="LBS/GAL"> 6.02 </density>
<type>AVGAS</type>
</tank>
<!-- 3: Strainer sump -->
<tank type="FUEL">
<location unit="IN">
<x>-0.28</x>
<y>0</y>
<z>-0.30</z>
</location>
<drain_location unit="M">
<x>-0.28</x>
<y>0</y>
<z>-0.50</z>
</drain_location>
<capacity unit="LBS">0.1</capacity>
<contents unit="LBS">0</contents>
<temperature>50</temperature>
<density unit="LBS/GAL"> 6.02 </density>
<type>AVGAS</type>
</tank>
<!-- 4: Fuel pipe -->
<tank type="FUEL">
<location unit="IN">
<x>-0.35</x>
<y>0</y>
<z>-0.30</z>
</location>
<drain_location unit="M">
<x>-0.35</x>
<y>0</y>
<z>-0.50</z>
</drain_location>
<capacity unit="LBS">0.05</capacity>
<contents unit="LBS">0</contents>
<temperature>50</temperature>
<density unit="LBS/GAL"> 6.02 </density>
<type>AVGAS</type>
</tank>
<!-- 5: engine manifold (engine feeds from here) -->
<tank type="FUEL">
<location unit="IN">
<x>-0.60</x>
<y>0</y>
<z>-0.30</z>
</location>
<drain_location unit="M">
<x>-0.60</x>
<y>0</y>
<z>-0.50</z>
</drain_location>
<capacity unit="LBS">0.1</capacity>
<contents unit="LBS">0</contents>
<temperature>50</temperature>
<density unit="LBS/GAL"> 6.02 </density>
<type>AVGAS</type>
</tank>
<!-- 6: "virtual" mix-to-engine tank (workaround for starter mixture) -->
<tank type="FUEL">
<location unit="IN">
<x>0</x>
<y>0</y>
<z>0</z>
</location>
<drain_location unit="M">
<x>0</x>
<y>0</y>
<z>0</z>
</drain_location>
<capacity unit="LBS">0.001</capacity>
<contents unit="LBS">0</contents>
<priority>0</priority>
</tank>
</propulsion>
<system file="fuel"/> <!-- integrate advanced fuel system -->
<system file="external-heat"/> <!-- integrate external-heater -->
<system file="electrical"/> <!-- load electrical system -->
<system file="cabin-heat_and_air"/> <!-- cabin heat and air -->
<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-->
<!-- following code by Jonathan Redpath aka legoboyvdlp-->
<channel name="NWS">
<switch name="fcs/nws-enabled">
<default value="0"/>
<test logic="OR" value="1"> <!-- NWS mechanically centered if gear is fully extended -->
/gear/gear[0]/compression-norm gt 0.001
</test>
</switch>
<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="fcs/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>
<switch name="fcs/brake-influence-enabled"> <!-- brake should not influence nws if the aircraft is not moving -->
<default value="0"/>
<test logic="OR" value="1">
/gear/gear[0]/rollspeed-ms gt 0.25
</test>
</switch>
<fcs_function name="fcs/brake-sum-adjusted">
<function>
<product>
<property>fcs/brake-influence-enabled</property>
<property>fcs/brake-sum</property>
</product>
</function>
</fcs_function>
<fcs_function name="fcs/nws-cmd-deg"> <!-- Drive the nose wheel with the rudder and brakes -->
<function>
<table>
<independentVar lookup="row">fcs/brake-sum-adjusted</independentVar>
<independentVar lookup="column">/controls/flight/rudder</independentVar>
<tableData>
-1 0 1
-1 -29 0 11
0 -11 0 11
1 -11 0 29
</tableData>
</table>
</function>
</fcs_function>
<fcs_function name="fcs/nws-cmd-deg-adjusted">
<function>
<product>
<property>fcs/nws-cmd-deg</property>
<property>fcs/nws-enabled</property>
</product>
</function>
</fcs_function>
<actuator name="fcs/steer-deg">
<input>fcs/nws-cmd-deg-adjusted</input>
<rate_limit>80</rate_limit> <!-- 80 deg / s , or 1/8 second to full deflection with NWS -->
<output>fcs/steer-pos-deg</output>
</actuator>
</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>
<output>fcs/roll-trim-sum</output>
</summer>
<summer name="Aileron Norm Left">
<input>fcs/roll-trim-sum</input>
<clipto>
<min>-1.0</min>
<max>1.0</max>
</clipto>
<output>fcs/left-aileron-pos-norm</output>
</summer>
<aerosurface_scale name="Left Aileron Control">
<input>fcs/roll-trim-sum</input>
<range>
<min>-0.349066</min>
<max>0.261799</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<summer name="Aileron Norm Right">
<input>fcs/roll-trim-sum</input>
<clipto>
<min>1.0</min>
<max>-1.0</max>
</clipto>
<output>fcs/right-aileron-pos-norm</output>
</summer>
<aerosurface_scale name="Right Aileron Control">
<input>fcs/roll-trim-sum</input>
<range>
<min>0.261799 </min>
<max>-0.349066</max>
</range>
<output>fcs/right-aileron-pos-rad</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">
<!-- Disable flap movement if electrical voltage is too low -->
<switch name="Flaps Command">
<default value="fcs/flap-cmd-norm"/>
<output>fcs/flap-input-norm</output>
<!-- Route back the (normalized) output of the <kinematic>
to its input in order to disable it.
-->
<test logic="AND" value="fcs/flap-pos-norm">
/systems/electrical/outputs/flaps le 16
</test>
</switch>
<kinematic name="Flaps Control">
<input>fcs/flap-input-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/c182s/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>
<!-- Defines cooling airflow with min=closed/max=open cowl flaps -->
<min>0.48</min>
<max>0.80</max>
</range>
<output>propulsion/engine[0]/cooling-factor-cowlflaps</output>
</aerosurface_scale>
<switch name="cooling-factor-winterkit">
<!-- winter kit reduces cooling airflow -->
<default value="1"/>
<test logic="AND" value="0.50">
/engines/engine/winter-kit-installed EQ 1
</test>
<output>propulsion/engine[0]/cooling-factor-winterkit</output>
</switch>
<aerosurface_scale name="icing-nose-air-inlet">
<!-- ice accumulation in nose inlets reduces cooling airflow -->
<input>/fdm/jsbsim/ice/fuselage</input> <!-- ice in inches -->
<gain>1.0</gain>
<zero_centered>false</zero_centered>
<domain>
<min>0.00</min>
<max>0.010</max> <!-- at this inch the max-range is output (thicker ice does not increase effect further) -->
</domain>
<range>
<!-- reducing factor: 1=no reduction/0=full blocked; min=no-ice, max=full-ice -->
<min>1.00</min>
<max>0.75</max>
</range>
<clipto>
<min>0.75</min>
<max>1.00</max>
</clipto>
<output>propulsion/engine[0]/cooling-factor-noseicing</output>
</aerosurface_scale>
<fcs_function name="engine-cooling-factor">
<function>
<product>
<property>propulsion/engine[0]/cooling-factor-winterkit</property>
<property>propulsion/engine[0]/cooling-factor-cowlflaps</property>
<property>propulsion/engine[0]/cooling-factor-noseicing</property>
</product>
</function>
<clipto>
<min>0</min>
<max>1</max>
</clipto>
<output>propulsion/engine[0]/cooling-factor</output> <!-- final cooling factor to engine -->
</fcs_function>
</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/c182s/cockpit/brake-lever</output>
</kinematic>
</channel>
</flight_control>
<aerodynamics>
<property value="0.0">ice/wing</property>
<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>
<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>
</function>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<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>
</function>
<function name="aero/function/vel-propwash-fps">
<description> propeller induced velocity </description>
<property>propulsion/engine/prop-induced-velocity_fps</property>
</function>
<function name="aero/function/qbar-propwash-psf">
<description> q bar due to the propeller induced velocity </description>
<product>
<property>aero/function/vel-propwash-fps</property>
<property>aero/function/vel-propwash-fps</property>
<property>atmosphere/rho-slugs_ft3</property>
<value>0.5</value>
</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>
</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>
<!--taken from SenecaII by Torsten Dreyer-->
<function name="aero/coefficient/CLicew">
<description>Lift_decrease_due_to_ice_on_wing</description>
<product>
<property>aero/qbar-area</property>
<table>
<independentVar>ice/wing</independentVar>
<tableData>
0.0 0
0.5 -0.6
1.0 -1.2
2.0 -2.4
</tableData>
</table>