jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<fdm_config name="DHC-6" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Erik Hofman </author>
<filecreationdate> 2003-01-01 </filecreationdate>
<version> $Id: DHC6.xml,v 1.21 2014/02/09 10:36:32 ehofman Exp $ </version>
<description> DeHavilland DHC-6 </description>
<reference title="http://www.aoc.noaa.gov/aircraft_otter.htm"/>
<reference title="Smart Icing Systems Aerodynamics group UIUC
https://gitorious.org/fg/fgdata/source/73c7e296676c55a4d1db43b49c3fcb938e991177:Aircraft-uiuc/TwinOtter"/>
<reference title="Current Methods for Modeling and Simulating Icing Effects on Aircraft Performance, Stability and Control
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090005992_2009004916.pdf"/>
<reference title="Simulation Model Development for Icing Effects Flight Training
http://www.bihrle.aero/pdfs/aiaa2002-01-1527.pdf"/>
<reference title="performance data of the DHC-6-300
http://www.caamsllc.com/Performance%20Data/DHC-6-300.pdf"/>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. If this model has been validated at all, it would be
only to the extent that it seems to "fly right", and that it possibly
complies with published, publicly known, performance data (maximum speed,
endurance, etc.). Thus, this model is meant for educational and entertainment
purposes only.
This simulation model is not endorsed by the manufacturer.
</note>
</fileheader>
<metrics>
<wingarea unit="FT2"> 422.5 </wingarea>
<wingspan unit="FT"> 65 </wingspan>
<chord unit="FT"> 6.5 </chord>
<htailarea unit="FT2"> 98.18 </htailarea>
<htailarm unit="FT"> 24.75 </htailarm>
<vtailarea unit="FT2"> 76.05 </vtailarea>
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x> 211.8 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 93.6 </x>
<y> -18.2 </y>
<z> 31.2 </z>
</location>
<location name="VRP" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 19317 </ixx>
<iyy unit="SLUG*FT2"> 24679 </iyy>
<izz unit="SLUG*FT2"> 35344 </izz>
<ixz unit="SLUG*FT2"> -1099 </ixz>
<emptywt unit="LBS"> 8100 </emptywt>
<location name="CG" unit="IN">
<x> 211.8 </x>
<y> 0 </y>
<z> -14.9 </z>
</location>
<pointmass name="name">
<weight unit="LBS"> 230 </weight>
<location name="POINTMASS" unit="IN">
<x> 93.6 </x>
<y> -18.2 </y>
<z> 8.4 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> 75.5 </x>
<y> 0 </y>
<z> -118.2 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 2982.6 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 994.2 </damping_coeff>
<max_steer unit="DEG"> 15 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MLG">
<location unit="IN">
<x> 245.9 </x>
<y> -77.3 </y>
<z> -117.5 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 9942 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1988.4 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>0</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MLG">
<location unit="IN">
<x> 245.9 </x>
<y> 77.3 </y>
<z> -117.5 </z>
</location>
<static_friction> 0.8 </static_friction>
<dynamic_friction> 0.5 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 9942 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1988.4 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="PT6A-27">
<location unit="IN">
<x> 142.4 </x>
<y> -109.3 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<thruster file="direct">
<location unit="IN">
<x> 142.4 </x>
<y> -109.3 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="PT6A-27">
<location unit="IN">
<x> 142.4 </x>
<y> 109.3 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>1</feed>
<feed>0</feed>
<thruster file="direct">
<location unit="IN">
<x> 142.4 </x>
<y> 109.3 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL"> <!-- Tank number 0 -->
<location unit="IN">
<x> 211.8 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 1290.5 </capacity>
<contents unit="LBS"> 892.1 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 1 -->
<location unit="IN">
<x> 211.8 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 1290.5 </capacity>
<contents unit="LBS"> 892.1 </contents>
</tank>
</propulsion>
<flight_control name="FCS: DHC-6 Twin Otter">
<channel name="Pitch">
<summer name="fcs/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="fcs/elevator-control">
<input>fcs/pitch-trim-sum</input>
<range>
<min>-0.454</min>
<max>0.244</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="fcs/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="fcs/left-aileron-control">
<input>fcs/roll-trim-sum</input>
<range>
<min>-0.28</min>
<max>0.33</max>
</range>
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="fcs/right-aileron-control">
<input>-fcs/roll-trim-sum</input>
<range>
<min>-0.28</min>
<max>0.33</max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="fcs/rudder-command-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="fcs/rudder-control">
<input>fcs/rudder-command-sum</input>
<range>
<min>-0.28</min>
<max>0.28</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
</channel>
<channel name="Flaps">
<kinematic name="fcs/flaps-control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>10</position>
<time>4</time>
</setting>
<setting>
<position>20</position>
<time>2</time>
</setting>
<setting>
<position>30</position>
<time>2</time>
</setting>
<setting>
<position>40</position>
<time>2</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="fcs/flap-position-normalizer">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min> <!-- Flaps actual minimum position -->
<max>40</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="Speedbrake">
<kinematic name="fcs/speedbrake-control">
<input>fcs/speedbrake-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>1</time>
</setting>
</traverse>
<output>fcs/speedbrake-pos-norm</output>
</kinematic>
</channel>
<channel name="Thrust">
<summer name="fcs/engine-thrust-lbs">
<input>propulsion/engine[0]/thrust-lbs</input>
<input>propulsion/engine[1]/thrust-lbs</input>
</summer>
<aerosurface_scale name="fcs/engine-thrust-control">
<input>fcs/engine-thrust-lbs</input>
<range>
<min>0.0</min>
<max>0.0001004</max>
<!-- 0.26/(1295+1295): CTmax = 0.26, 1295 lbs per engine -->
</range>
<output>fcs/engine-thrust-coefficient</output>
</aerosurface_scale>
</channel>
</flight_control>
<aerodynamics>
<axis name="DRAG">
<function name="aero/coefficient/CD0">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-1.5700 1.6590
-0.2600 0.0580
0.0000 0.0488
0.2600 0.0580
1.5700 1.6590
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDi">
<description>Induced_drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<value>0.0390</value>
</product>
</function>
<function name="aero/coefficient/CDmach">
<description>Drag_due_to_mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0000
0.7000 0.0000
1.1000 0.0230
1.8000 0.0150
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDflap">
<description>Drag_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-norm</property>
<value>0.0350</value>
</product>
</function>
<function name="aero/coefficient/CDsb">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.0280</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>
<table>
<independentVar>aero/mag-beta-rad</independentVar>
<tableData>
0.0000 0.0000
0.2600 0.0500
1.5700 1.2300
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDde">
<description>Drag_due_to_Elevator_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-norm</property>
<value>0.0350</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/coefficient/CYb">
<description>Side_force_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<value>-0.6000</value>
</product>
</function>
<function name="aero/coefficient/CYdr">
<description>Side_force_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value>0.1500</value>
</product>
</function>
<function name="aero/coefficient/CYp">
<description>Side_force_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.2000</value>
</product>
</function>
<function name="aero/coefficient/CYr">
<description>Side_force_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.4000</value>
</product>
</function>
</axis>
<axis name="LIFT">
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.3491 -0.5800
-0.2618 -0.5200
-0.1745 -0.4500
-0.1396 -0.2800
-0.1047 -0.2000
-0.0698 0.1600
-0.0349 0.3200
0.0000 0.4400
0.0349 0.5800
0.0698 0.7500
0.1047 0.8100
0.1396 0.9500
0.1745 1.1000
0.2094 1.1250
0.2443 1.1400
0.2793 1.1600
0.3142 1.1200
0.3491 1.1300
0.4363 1.1700
0.5236 1.2099
0.6109 1.2699
0.6981 1.3999
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLflap">
<description>Delta_Lift_due_to_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.0000
10.0000 0.9250
20.0000 1.1890
30.0000 1.4750
40.0000 1.6330
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLsb">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.0000</value>
</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>0.6080</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>19.9700</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 lookup="row">aero/beta-rad</independentVar>
<independentVar lookup="column">aero/alpha-rad</independentVar>
<tableData>
0.0698 0.1745 0.2443 0.3491
-0.3491 0.1250 0.0450 0.0240 -0.0270
-0.2618 0.0900 0.0220 0.0030 -0.0150
-0.1745 0.0770 0.0200 -0.0100 0.0000
-0.0873 0.0360 0.0270 -0.0220 -0.0080
0.0000 0.0000 -0.0100 0.0200 -0.0060
0.0873 0.0360 -0.0170 0.0200 -0.0100
0.1745 0.0770 -0.0100 0.0050 -0.0100
0.2618 0.0900 -0.0250 -0.0180 0.0000
0.3491 0.1250 -0.0450 -0.0350 0.0200
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_moment_due_to_roll_rate_(roll_damping)</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.5000</value>
<!--
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 20.0 40.0
0.0000 -0.4078 0.2897 0.4123
0.1745 -0.1537 0.1054 0.0251
0.2618 -0.0055 0.0029 0.0057
0.3491 0.0657 -0.0476 -0.0669
</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>
<value>0.0600</value>
</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.1500
2.0000 0.0500
</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>0.0150</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cma">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-0.3491 0.391
-0.2618 0.423
-0.1745 0.288
-0.0873 0.189
0.0000 0.093
0.0873 -0.048
0.1745 -0.200
0.2618 -0.318
0.3491 -0.384
0.4363 -0.397
0.5236 -0.403
0.6109 -0.469
0.6981 -0.532
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmDe">
<description>Pitch_moment_due_to_elevator_and_flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
<independentVar lookup="table">fcs/flap-pos-deg</independentVar>
<tableData breakPoint="0.0">
-0.4538 -0.2269 0.0000 0.1222 0.2443
-0.3491 0.2800 0.1700 0.0000 -0.1000 -0.2200
-0.2618 0.2000 0.0900 0.0000 -0.0900 -0.2800
-0.1745 0.4300 0.3100 0.0000 -0.1700 -0.3700
-0.1396 0.5100 0.3700 0.0000 -0.1900 -0.3800
-0.1047 0.5300 0.3900 0.0000 -0.2000 -0.3800
-0.0698 0.5600 0.4000 0.0000 -0.2000 -0.3900
-0.0349 0.5900 0.4100 0.0000 -0.2000 -0.3800
0.0000 0.6300 0.4000 0.0000 -0.1900 -0.3800
0.0349 0.6400 0.3900 0.0000 -0.2000 -0.3600
0.0698 0.6500 0.4000 0.0000 -0.1900 -0.3400
0.1047 0.6400 0.3800 0.0000 -0.1800 -0.3200
0.1396 0.5800 0.3600 0.0000 -0.1600 -0.3200
0.1745 0.5900 0.3700 0.0000 -0.2100 -0.3200
0.2094 0.5600 0.3500 0.0000 -0.2100 -0.3400
0.2443 0.5400 0.3400 0.0000 -0.1900 -0.2900
0.2793 0.4800 0.3300 0.0000 -0.1700 -0.2600
0.3142 0.4300 0.3100 0.0000 -0.1500 -0.2300
0.3491 0.4600 0.3000 0.0000 -0.2100 -0.2000
0.4363 0.2600 0.2100 0.0000 -0.0800 -0.1400
0.5236 0.2900 0.1900 0.0000 -0.0900 -0.1900
0.6109 0.3800 0.2400 0.0000 -0.0800 -0.1600
0.6981 0.4200 0.2300 0.0000 -0.0900 -0.1800
</tableData>
<tableData breakPoint="20.0">
-0.4538 -0.2269 0.0000 0.1222 0.2443
-0.3491 0.3300 0.1800 0.0000 -0.4000 -0.1900
-0.2618 0.3000 0.2100 0.0000 -0.2000 -0.2200
-0.1745 0.4400 0.2400 0.0000 -0.1500 -0.3800
-0.1396 0.4800 0.2800 0.0000 -0.1700 -0.3600
-0.1047 0.4700 0.3000 0.0000 -0.1700 -0.3500
-0.0698 0.4600 0.3200 0.0000 -0.1900 -0.3700
-0.0349 0.4500 0.3500 0.0000 -0.2000 -0.3900
0.0000 0.5300 0.3600 0.0000 -0.2000 -0.4000
0.0349 0.5700 0.3800 0.0000 -0.2000 -0.3800
0.0698 0.5900 0.3900 0.0000 -0.2000 -0.3600
0.1047 0.6200 0.3800 0.0000 -0.2000 -0.3500
0.1396 0.5700 0.3500 0.0000 -0.1500 -0.2900
0.1745 0.4900 0.2900 0.0000 -0.1300 -0.2800
0.2094 0.4700 0.2700 0.0000 -0.1200 -0.2700
0.2443 0.4500 0.2500 0.0000 -0.1300 -0.2700
0.2793 0.4100 0.2300 0.0000 -0.1400 -0.2800
0.3142 0.4200 0.2500 0.0000 -0.1200 -0.3100
0.3491 0.4100 0.2300 0.0000 -0.1500 -0.2700
0.4363 0.3200 0.1900 0.0000 -0.0900 -0.1300
0.5236 0.2400 0.2000 0.0000 -0.0600 -0.1300
0.6109 0.2700 0.1600 0.0000 -0.0800 -0.1700
0.6981 0.3600 0.2100 0.0000 -0.0700 -0.1500
</tableData>
<tableData breakPoint="40.0">
-0.4538 -0.2269 0.0000 0.1222 0.2443
-0.3491 0.2900 0.1700 0.0000 -0.0700 -0.2200
-0.2618 0.2000 0.0900 0.0000 -0.0700 -0.2600
-0.1745 0.1800 0.2100 0.0000 -0.1600 -0.3200
-0.1396 0.3600 0.2900 0.0000 -0.1800 -0.3600
-0.1047 0.4800 0.3300 0.0000 -0.2000 -0.3800
-0.0698 0.5000 0.3600 0.0000 -0.2000 -0.3800
-0.0349 0.5300 0.3700 0.0000 -0.2000 -0.3600
0.0000 0.5600 0.3800 0.0000 -0.1900 -0.3400
0.0349 0.6000 0.3900 0.0000 -0.1700 -0.2900
0.0698 0.6400 0.2600 0.0000 -0.1500 -0.2600
0.1047 0.5900 0.2400 0.0000 -0.1300 -0.2400
0.1396 0.5300 0.2400 0.0000 -0.1100 -0.2000
0.1745 0.4200 0.2200 0.0000 -0.1000 -0.2100
0.2094 0.4100 0.2100 0.0000 -0.1100 -0.2400
0.2443 0.4400 0.2200 0.0000 -0.1300 -0.2300
0.2793 0.4200 0.2500 0.0000 -0.1100 -0.2000
0.3142 0.4800 0.2800 0.0000 -0.1000 -0.2000
0.3491 0.1800 0.2100 0.0000 -0.0800 -0.1900
0.4363 0.2400 0.1900 0.0000 -0.1200 -0.1600
0.5236 0.2800 0.1800 0.0000 -0.0700 -0.1400
0.6109 0.3600 0.1800 0.0000 -0.1000 -0.1700
0.6981 0.3900 0.2100 0.0000 -0.0900 -0.1300
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmT">
<description>Pitch_moment_due_to_propulsion</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/engine-thrust-coefficient</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.00 40.00
-0.3491 0.0000 0.0000
-0.2618 0.0013 0.0489
-0.1745 0.0097 0.0792
-0.0873 0.0384 0.0467
0.0000 0.0411 0.0879
0.0873 0.0598 0.2875
0.1745 0.1179 0.3201
0.2618 0.1803 0.0000
0.3491 0.1452 0.0000
0.4363 0.0000 0.0000
0.5236 0.0000 0.0000
0.6109 0.0000 0.0000
0.6981 0.0000 0.0000
</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>-34.2000</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>-8.0000</value>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 20.0 40.0
-0.3491 -0.6000 -0.6000 -0.6000
-0.2618 -0.5150 -0.5150 -0.5150
-0.1745 -0.4750 0.0000 0.5923
-0.0873 0.0010 0.5897 1.4987
0.0000 0.5000 1.2032 2.4329
0.0873 0.8670 1.0046 2.8111
0.1745 1.1575 2.2389 3.1892
0.2618 1.1768 2.4895 2.8321
0.3491 1.0080 2.1187 2.5586
0.4363 1.1973 1.9986 2.1203
0.5236 1.1249 1.7488 1.9943
0.6109 1.2786 1.7401 1.8735
0.6981 1.4377 1.7387 1.7387
</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>-0.1800</value>
</product>
</function>
<function name="aero/coefficient/Cnp">
<description>Yaw_moment_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value>-0.0600</value>
</product>
</function>
<function name="aero/coefficient/Cndr">
<description>Yaw_moment_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value>-0.1250</value>
</product>
</function>
<function name="aero/coefficient/Cnda">
<description>Adverse_yaw</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/left-aileron-pos-rad</property>
<value>-0.0010</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>