1ab65221b1
https://github.com/Juanvvc/c172p-detailed commit 874b89fedff35dfe1967e09365d3cb0d5b11522c
1685 lines
66 KiB
XML
1685 lines
66 KiB
XML
<?xml version="1.0"?>
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<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
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<!-- Source: http://forum.flightgear.org/viewtopic.php?f=25&t=21664&start=45 -->
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<fdm_config name="c172" version="2.0" release="BETA"
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xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
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xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
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<fileheader>
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<author> Unknown </author>
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<filecreationdate> 2002-01-01 </filecreationdate>
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<version> $Id: c172p.xml,v 1.40 June 2015 $ </version>
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<!-- experimental stall and spin, up to flat spin March 2014 -->
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<!-- Source: http://forum.flightgear.org/viewtopic.php?f=25&t=21664&start=45 -->
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<!-- this file with comments for stall and spin to help -->
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<!-- further modifications for c172p-detailed 2015 -->
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<!-- FOR TESTS, Two-engine and Propeller choice, dany june 2015-->
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<!--
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For 180 hp, engine[1]:
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**Manually** set Internal Properties /controls/engines/engine[1]/magnetos = 3
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better to set original magnetos to 0 (key)
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do not use "s" (would start engine[0], 160 hp)
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start with controls/engines/engine[1]/starter = 1 then back to 0, or Ctrl-click on "starter = ", twice to stop starter
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-->
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<description> Cessna C-172 </description>
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</fileheader>
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<metrics>
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<wingarea unit="FT2"> 174 </wingarea>
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<wingspan unit="FT"> 35.8 </wingspan>
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<chord unit="FT"> 4.9 </chord>
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<htailarea unit="FT2"> 21.9 </htailarea>
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<htailarm unit="FT"> 15.7 </htailarm>
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<vtailarea unit="FT2"> 16.5 </vtailarea>
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<vtailarm unit="FT"> 0 </vtailarm>
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<location name="AERORP" unit="IN">
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<x> 47 </x>
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<y> 0 </y>
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<z> 59.4 </z>
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</location>
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<location name="EYEPOINT" unit="IN">
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<x> 37 </x>
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<y> 0 </y>
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<z> 48 </z>
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</location>
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<location name="VRP" unit="IN">
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<x> 42.6 </x>
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<y> 0 </y>
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<z> 38.5 </z>
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</location>
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</metrics>
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<mass_balance>
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<ixx unit="SLUG*FT2"> 948 </ixx>
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<iyy unit="SLUG*FT2"> 1346 </iyy>
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<izz unit="SLUG*FT2"> 1967 </izz>
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<ixy unit="SLUG*FT2"> -0 </ixy>
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<ixz unit="SLUG*FT2"> -0 </ixz>
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<iyz unit="SLUG*FT2"> -0 </iyz>
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<emptywt unit="LBS"> 1500 </emptywt>
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<location name="CG" unit="IN">
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<x> 41 </x>
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<y> 0 </y>
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<z> 36.5 </z>
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</location>
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<pointmass name="Pilot">
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<weight unit="LBS"> 180 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 36 </x>
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<y> -14 </y>
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<z> 24 </z>
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</location>
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</pointmass>
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<pointmass name="Co-Pilot">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 36 </x>
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<y> 14 </y>
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<z> 24 </z>
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</location>
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</pointmass>
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<pointmass name="Left Passenger">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 70 </x>
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<y> -14 </y>
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<z> 24 </z>
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</location>
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</pointmass>
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<pointmass name="Right Passenger">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 70 </x>
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<y> 14 </y>
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<z> 24 </z>
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</location>
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</pointmass>
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<pointmass name="Baggage">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 95 </x>
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<y> 0 </y>
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<z> 24 </z>
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</location>
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</pointmass>
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<!-- Bushkits 1 to 4, pointmass [5] to [12] -->
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<!-- Weight and drag are managed by Systems/bushkit.xml -->
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<pointmass name="Left bush wheel 26 inches">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 58.2 </x>
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<y> -43 </y>
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<z> -15.5 </z>
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</location>
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</pointmass>
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<pointmass name="Right bush wheel 26 inches">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 58.2 </x>
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<y> 43 </y>
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<z> -15.5 </z>
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</location>
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</pointmass>
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<pointmass name="Left bush wheel 36 inches">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 58.2 </x>
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<y> -43 </y>
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<z> -15.5 </z>
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</location>
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</pointmass>
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<pointmass name="Right bush wheel 36 inches">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 58.2 </x>
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<y> 43 </y>
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<z> -15.5 </z>
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</location>
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</pointmass>
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<pointmass name="Left float">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 41 </x>
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<y> -43 </y>
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<z> -25 </z>
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</location>
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</pointmass>
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<pointmass name="Right float">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 41 </x>
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<y> 43 </y>
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<z> -25 </z>
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</location>
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</pointmass>
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<pointmass name="Left amphibious">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 41 </x>
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<y> -43 </y>
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<z> -25 </z>
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</location>
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</pointmass>
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<pointmass name="Right amphibious">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 41 </x>
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<y> 43 </y>
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<z> -25 </z>
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</location>
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</pointmass>
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<!-- Extra weight due to 180 hp engine, pointmass [13]; managed by Systems/bushkit.xml -->
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<!-- x location for empty CG at 38.1", cf. 552SP POH p.6-12, Weight and moment tabulation: 1642 lbs, 62600 lb-ins -->
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<pointmass name="extra weight 180hp">
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<weight unit="LBS"> 0 </weight>
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<location name="POINTMASS" unit="IN">
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<x> 7.75 </x>
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<y> 0 </y>
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<z> 26.6 </z>
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</location>
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</pointmass>
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</mass_balance>
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<ground_reactions>
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<documentation>
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The hydrodynamic interactions of the floats are modelled by
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external forces.
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</documentation>
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<contact type="BOGEY" name="NOSE">
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<location unit="IN">
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<x> -6.8 </x>
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<y> 0 </y>
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<z> -19.5 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<rolling_friction> 0.02 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 1800 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
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<max_steer unit="DEG"> 10 </max_steer>
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<brake_group> NONE </brake_group>
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<retractable>0</retractable>
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</contact>
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<contact type="BOGEY" name="LEFT_MAIN">
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<location unit="IN">
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<x> 58.2 </x>
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<y> -43 </y>
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<z> -15.5 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<rolling_friction> 0.02 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 400 </damping_coeff>
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<max_steer unit="DEG"> 0.0 </max_steer>
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<brake_group> LEFT </brake_group>
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<retractable>0</retractable>
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</contact>
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<contact type="BOGEY" name="RIGHT_MAIN">
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<location unit="IN">
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<x> 58.2 </x>
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<y> 43 </y>
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<z> -15.5 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<rolling_friction> 0.02 </rolling_friction>
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<spring_coeff unit="LBS/FT"> 5400 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 400 </damping_coeff>
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<max_steer unit="DEG"> 0.0 </max_steer>
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<brake_group> RIGHT </brake_group>
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<retractable>0</retractable>
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</contact>
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<!-- Damage Mod -->
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<!-- contact 3, 4, 5 -->
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<contact type="STRUCTURE" name="TAIL_SKID">
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<location unit="IN">
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<x> 226.7 </x>
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<y> 0 </y>
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<z> 8 </z>
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</location>
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<static_friction> 0.5 </static_friction>
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<dynamic_friction> 0.25 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 2000 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="LEFT_TIP">
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<location unit="IN">
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<x> 20 </x>
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<y> -232 </y>
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<z> 50 </z>
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</location>
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<static_friction> 0.75 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="RIGHT_TIP">
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<location unit="IN">
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<x> 20 </x>
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<y> 232 </y>
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<z> 50 </z>
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</location>
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<static_friction> 0.75 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<!-- contact 6, 7, 8 -->
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<contact type="STRUCTURE" name="FRONT_BROKEN_GEAR">
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<location unit="IN">
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<x> -6.8 </x>
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<y> 0 </y>
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<z> 0 </z>
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</location>
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<static_friction> 0.9 </static_friction>
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<dynamic_friction> 0.5 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="LEFT_BROKEN_GEAR">
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<location unit="IN">
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<x> 58.2 </x>
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<y> -48 </y>
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<z> 0 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.4 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="RIGHT_BROKEN_GEAR">
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<location unit="IN">
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<x> 58.2 </x>
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<y> 48 </y>
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<z> 0 </z>
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</location>
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<static_friction> 0.8 </static_friction>
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<dynamic_friction> 0.4 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<!-- contact 9, 10, 11, 12 -->
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<contact type="STRUCTURE" name="NOSE_TOP">
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<location unit="IN">
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<x> -119 </x>
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<y> 0 </y>
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<z> 35 </z>
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</location>
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<static_friction> .75 </static_friction>
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<dynamic_friction> .5 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="NOSE">
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<location unit="IN">
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<x> -119 </x>
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<y> 0 </y>
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<z> 8 </z>
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</location>
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<static_friction> 3.0 </static_friction>
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<dynamic_friction> 2.0 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="COCKPIT_TOP">
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<location unit="IN">
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<x> -4.7 </x>
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<y> 0 </y>
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<z> 60 </z>
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</location>
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<static_friction> 3.0 </static_friction>
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<dynamic_friction> 2.0 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="TOP_VS">
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<location unit="IN">
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<x> 253.5 </x>
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<y> 0 </y>
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<z> 90 </z>
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</location>
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<static_friction> 3.0 </static_friction>
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<dynamic_friction> 2.0 </dynamic_friction>
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<spring_coeff unit="LBS/FT"> 1830.15 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 366.03 </damping_coeff>
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</contact>
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<!-- contact 13, 14, 15, 16, 17, 18 -->
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<contact type="STRUCTURE" name="LFfloat">
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<location unit="IN">
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<x>3.230</x>
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<y>-56.889</y>
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<z>38.5</z>
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</location>
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<static_friction>0.6</static_friction>
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<dynamic_friction>0.5</dynamic_friction>
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<spring_coeff unit="LBS/FT">10000.00 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC">2500.00 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="RFfloat">
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<location unit="IN">
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<x>3.230</x>
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<y>56.889</y>
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<z>38.5</z>
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</location>
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<static_friction>0.6</static_friction>
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<dynamic_friction>0.5</dynamic_friction>
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<spring_coeff unit="LBS/FT">10000.00 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC">2500.00 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="LMfloat">
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<location unit="IN">
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<x>70.16</x>
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<y>-56.889</y>
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<z>38.5</z>
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</location>
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<static_friction>0.6</static_friction>
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<dynamic_friction>0.5</dynamic_friction>
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<spring_coeff unit="LBS/FT">10000.00 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC">2500.00 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="RMfloat">
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<location unit="IN">
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<x>70.16</x>
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<y>56.889</y>
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<z>38.5</z>
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</location>
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<static_friction>0.6</static_friction>
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<dynamic_friction>0.5</dynamic_friction>
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<spring_coeff unit="LBS/FT">10000.00 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC">2500.00 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="LRfloat">
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<location unit="IN">
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<x>160.71</x>
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<y>-56.889</y>
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<z>38.5</z>
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</location>
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<static_friction>0.6</static_friction>
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<dynamic_friction>0.5</dynamic_friction>
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<spring_coeff unit="LBS/FT">10000.00 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC">2500.00 </damping_coeff>
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</contact>
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<contact type="STRUCTURE" name="RRfloat">
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<location unit="IN">
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<x>160.71</x>
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<y>56.889</y>
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<z>38.5</z>
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</location>
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<static_friction>0.6</static_friction>
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<dynamic_friction>0.5</dynamic_friction>
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<spring_coeff unit="LBS/FT">10000.00 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC">2500.00 </damping_coeff>
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</contact>
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<!-- contact 19, 20, 21, 22 -->
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<contact type="BOGEY" name="LFFloatGear">
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<location unit="IN">
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<x>-78</x>
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<y>-56.889</y>
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<z>0</z>
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</location>
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<static_friction>0.80 </static_friction>
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<dynamic_friction>0.50</dynamic_friction>
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<rolling_friction>0.02</rolling_friction>
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<spring_coeff unit="LBS/FT"> 1000 </spring_coeff>
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<damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
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<max_steer unit="DEG">360</max_steer>
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<brake_group>NONE</brake_group>
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<retractable>1</retractable>
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</contact>
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<contact type="BOGEY" name="RFFloatGear">
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<location unit="IN">
|
|
<x>-78</x>
|
|
<y>56.889</y>
|
|
<z>0</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"> 1000 </spring_coeff>
|
|
<damping_coeff unit="LBS/FT/SEC"> 600 </damping_coeff>
|
|
<max_steer unit="DEG">360</max_steer>
|
|
<brake_group>NONE</brake_group>
|
|
<retractable>1</retractable>
|
|
</contact>
|
|
<contact type="BOGEY" name="LMFloatGear">
|
|
<location unit="IN">
|
|
<x>76</x>
|
|
<y>-56.889</y>
|
|
<z>0</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"> 5400 </spring_coeff>
|
|
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
|
|
<max_steer unit="DEG">0</max_steer>
|
|
<brake_group>LEFT</brake_group>
|
|
<retractable>1</retractable>
|
|
</contact>
|
|
<contact type="BOGEY" name="RMFloatGear">
|
|
<location unit="IN">
|
|
<x>76</x>
|
|
<y>56.889</y>
|
|
<z>0</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"> 5400 </spring_coeff>
|
|
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
|
|
<max_steer unit="DEG">0</max_steer>
|
|
<brake_group>RIGHT</brake_group>
|
|
<retractable>1</retractable>
|
|
</contact>
|
|
</ground_reactions>
|
|
|
|
<propulsion>
|
|
<engine file="eng_io320">
|
|
<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>2</feed> <!-- from intermediate tank (float chamber 2) -->
|
|
<thruster file="prop_75in2f">
|
|
<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>
|
|
|
|
<engine file="eng_io360">
|
|
<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>3</feed> <!-- from intermediate tank (float chamber 3) -->
|
|
<!-- <thruster file="prop_76in2f_NACA_15-25deg"> -->
|
|
<thruster file="prop_76in2f_NACA_20deg">
|
|
<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 number 0 -->
|
|
<tank type="FUEL">
|
|
<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 number 1 -->
|
|
<tank type="FUEL">
|
|
<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 number 2, Float chamber -->
|
|
<tank type="FUEL">
|
|
<location unit="IN">
|
|
<x> 56 </x>
|
|
<y> 0 </y>
|
|
<z> 59.4 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 0.1 </capacity>
|
|
<contents unit="LBS"> 0 </contents>
|
|
<priority>1</priority>
|
|
</tank>
|
|
|
|
<!-- Tank number 3, Float chamber -->
|
|
<tank type="FUEL">
|
|
<location unit="IN">
|
|
<x> 56 </x>
|
|
<y> 0 </y>
|
|
<z> 59.4 </z>
|
|
</location>
|
|
<capacity unit="LBS"> 0.1 </capacity>
|
|
<contents unit="LBS"> 0 </contents>
|
|
<priority>1</priority>
|
|
</tank>
|
|
</propulsion>
|
|
|
|
<flight_control name="FCS: c172">
|
|
<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>-25</min>
|
|
<max>25</max>
|
|
</range>
|
|
<output>fcs/rudder-pos-rad</output>
|
|
</aerosurface_scale>
|
|
|
|
<aerosurface_scale name="Rudder Position Normalized">
|
|
<input>fcs/rudder-pos-deg</input>
|
|
<domain>
|
|
<min>-25</min>
|
|
<max>25</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>
|
|
|
|
<channel name="Mixture">
|
|
<!-- If the engine was primed enough times and throttle
|
|
is in starter position, then mixture is 1.
|
|
-->
|
|
<fcs_function name="fcs/mixture-primer">
|
|
<function>
|
|
<table>
|
|
<independentVar lookup="row">/controls/engines/engine/primer</independentVar>
|
|
<independentVar lookup="column">/controls/engines/current-engine/throttle</independentVar>
|
|
<tableData>
|
|
0.09 0.1 0.5 0.51
|
|
2 0 0 0 0
|
|
3 0 1 1 0
|
|
4 0 1 1 0
|
|
5 0 1 1 0
|
|
6 0 1 1 0
|
|
7 0 0 0 0
|
|
</tableData>
|
|
</table>
|
|
</function>
|
|
</fcs_function>
|
|
|
|
<!-- Primer logic for 160 HP engine -->
|
|
<switch name="Mixture Position 160 HP">
|
|
<default value="fcs/mixture-cmd-norm[0]"/>
|
|
<output>fcs/mixture-pos-norm[0]</output>
|
|
<!-- Use primer if used and engine is cold. If engine
|
|
is warm, then the mixture lever is used.
|
|
-->
|
|
<test logic="AND" value="fcs/mixture-primer">
|
|
/controls/engines/engine/use-primer eq 1
|
|
/engines/engine[0]/oil-temperature-degf le 75
|
|
</test>
|
|
</switch>
|
|
|
|
<!-- Primer logic for 180 HP engine -->
|
|
<switch name="Mixture Position 180 HP">
|
|
<default value="fcs/mixture-cmd-norm[1]"/>
|
|
<output>fcs/mixture-pos-norm[1]</output>
|
|
<!-- Use primer if used and engine is cold. If engine
|
|
is warm, then the mixture lever is used.
|
|
-->
|
|
<test logic="AND" value="fcs/mixture-primer">
|
|
/controls/engines/engine/use-primer eq 1
|
|
/engines/engine[1]/oil-temperature-degf le 75
|
|
</test>
|
|
</switch>
|
|
</channel>
|
|
|
|
<channel name="Landing Gear">
|
|
<kinematic name="Gr">
|
|
<input>gear/gear-cmd-norm</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>0</position>
|
|
<time>0 </time>
|
|
</setting>
|
|
<setting>
|
|
<position>1</position>
|
|
<time>5</time>
|
|
</setting>
|
|
</traverse>
|
|
<output>gear/gear-pos-norm</output>
|
|
</kinematic>
|
|
|
|
<kinematic name="/controls/gear/water-rudder-down">
|
|
<input>/controls/gear/water-rudder</input>
|
|
<traverse>
|
|
<setting>
|
|
<position>0</position>
|
|
<time>0 </time>
|
|
</setting>
|
|
<setting>
|
|
<position>1</position>
|
|
<time>5</time>
|
|
</setting>
|
|
</traverse>
|
|
</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>
|
|
</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>
|
|
</sum>
|
|
</function>
|
|
|
|
<function name="aero/function/qbar-induced-psf">
|
|
<description> q bar including the propulsion induced velocity.</description>
|
|
<product>
|
|
<property>aero/function/velocity-induced-fps</property>
|
|
<property>aero/function/velocity-induced-fps</property>
|
|
<property>atmosphere/rho-slugs_ft3</property>
|
|
<value>0.5</value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/function/total-wing-damage">
|
|
<description>Total damage on wings</description>
|
|
<product>
|
|
<sum>
|
|
<property>wing-damage/left-wing</property>
|
|
<property>wing-damage/right-wing</property>
|
|
</sum>
|
|
<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>
|
|
<property>gear/drag-coef[1]</property> <!-- bush wheels 26" -->
|
|
<property>gear/drag-coef[2]</property> <!-- bush wheels 36" -->
|
|
<property>gear/drag-coef[3]</property> <!-- Floats -->
|
|
<property>gear/drag-coef[4]</property> <!-- Amphibious -->
|
|
</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 10 20 30
|
|
-0.0873 0.0041 0 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 0.002 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 0.024 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 0.124 0.1343
|
|
0.1396 0.086 0.1232 0.1442 0.1554
|
|
0.1571 0.0962 0.1353 0.1573 0.169
|
|
0.1745 0.1069 0.1479 0.1708 0.183
|
|
0.1920 0.118 0.161 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
|
|
0.3491 0.2537 0.3298 0.3755 0.3983
|
|
0.5236 0.45 0.585 0.666 0.7065
|
|
0.6981 0.7 0.91 1.036 1.099
|
|
0.8727 1 1.3 1.48 1.57
|
|
1.0472 1.35 1.755 1.998 2.1195
|
|
1.2217 1.5 1.95 2.22 2.355
|
|
1.3963 1.57 2.041 2.3236 2.4649
|
|
1.5710 1.6 2.08 2.368 2.512
|
|
</tableData>
|
|
</table>
|
|
<property>gear/drag-coef[1]</property>
|
|
<property>gear/drag-coef[2]</property>
|
|
<property>gear/drag-coef[3]</property>
|
|
<property>gear/drag-coef[4]</property>
|
|
</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>
|
|
<property>gear/drag-coef[1]</property>
|
|
<property>gear/drag-coef[2]</property>
|
|
<property>gear/drag-coef[3]</property>
|
|
<property>gear/drag-coef[4]</property>
|
|
</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/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>0.0374</value>
|
|
</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>
|
|
0.00 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>
|
|
<table>
|
|
<independentVar>aero/function/total-wing-damage</independentVar>
|
|
<tableData>
|
|
0.0000 1
|
|
1.0000 0
|
|
</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>
|
|
<value>0.25</value>
|
|
</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 lookup="row">fcs/flap-pos-deg</independentVar>
|
|
<tableData>
|
|
0.0000 0.0798
|
|
30 0.1246
|
|
</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>
|
|
<table>
|
|
<independentVar>aero/function/total-wing-damage</independentVar>
|
|
<tableData>
|
|
0.0000 1
|
|
1.0000 0
|
|
</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>
|
|
|
|
<function name="aero/coefficient/Cllwdmg">
|
|
<description>Roll_moment_due_to_damaged_left_wing</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>wing-damage/left-wing</property>
|
|
<value>-0.3</value>
|
|
</product>
|
|
</function>
|
|
|
|
<function name="aero/coefficient/Clrwdmg">
|
|
<description>Roll_moment_due_to_damaged_right_wing</description>
|
|
<product>
|
|
<property>aero/qbar-psf</property>
|
|
<property>metrics/Sw-sqft</property>
|
|
<property>metrics/bw-ft</property>
|
|
<property>wing-damage/right-wing</property>
|
|
<value>0.3</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>
|
|
<!--
|
|
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>
|
|
<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>-1.8</value>
|
|
<!--
|
|
stall and spin (6):
|
|
elevator loss of efficiency when stalled
|
|
-->
|
|
<table>
|
|
<independentVar lookup="row">aero/alpha-deg</independentVar>
|
|
<tableData>
|
|
18 1
|
|
25 0.5
|
|
35 0.2
|
|
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
|
|
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/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/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>
|
|
<value>-0.016</value>
|
|
<table>
|
|
<independentVar>aero/function/total-wing-damage</independentVar>
|
|
<tableData>
|
|
0.0000 1
|
|
1.0000 0
|
|
</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>
|
|
<value>-0.07</value>
|
|
</product>
|
|
</function>
|
|
</axis>
|
|
|
|
</aerodynamics>
|
|
|
|
<external_reactions>
|
|
<force name="hydro-X" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y> 0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 1.0 </x>
|
|
<y> 0.0 </y>
|
|
<z> 0.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-Y" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y> 0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 0.0 </x>
|
|
<y> 1.0 </y>
|
|
<z> 0.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-Z" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y> 0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 0.0 </x>
|
|
<y> 0.0 </y>
|
|
<z>-1.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-pitch[0]" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 20.6 </x>
|
|
<y> 0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 0.0 </x>
|
|
<y> 0.0 </y>
|
|
<z>-1.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-pitch[1]" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 44.6 </x>
|
|
<y> 0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 0.0 </x>
|
|
<y> 0.0 </y>
|
|
<z>-1.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-yaw[0]" frame="BODY">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y>-12.0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 1.0 </x>
|
|
<y> 0.0 </y>
|
|
<z> 0.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-yaw[1]" frame="BODY">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y> 12.0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 1.0 </x>
|
|
<y> 0.0 </y>
|
|
<z> 0.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-roll[0]" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y>-12.0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 0.0 </x>
|
|
<y> 0.0 </y>
|
|
<z>-1.0 </z>
|
|
</direction>
|
|
</force>
|
|
<force name="hydro-roll[1]" frame="LOCAL">
|
|
<location unit="IN">
|
|
<x> 32.6 </x>
|
|
<y> 12.0 </y>
|
|
<z> 38.5 </z>
|
|
</location>
|
|
<direction>
|
|
<x> 0.0 </x>
|
|
<y> 0.0 </y>
|
|
<z>-1.0 </z>
|
|
</direction>
|
|
</force>
|
|
</external_reactions>
|
|
|
|
<system file="bushkit"/>
|
|
<system file="fuel"/>
|
|
<system file="hydrodynamics"/>
|
|
<system file="c172p-hydrodynamics"/>
|
|
<system file="c172p-ground-effects"/>
|
|
<system file="c172p-damage"/>
|
|
<system file="c172p-sounds"/>
|
|
|
|
<!--
|
|
<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>
|