jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<fdm_config name="Fokker-100" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Erik Hofman </author>
<filecreationdate>2010-08-08</filecreationdate>
<version>$Revision: 1.32 $</version>
<description> Fokker-100 commercial airliner </description>
<reference title="Butterworth-Heinemann - Civil Jet Aircraft Design (BH)
http://www.elsevierdirect.com/companions/9780340741528/appendices/data-a/table-8/table.htm"/>
<reference title="Lissys - PIANO aircraft analysis software
http://www.lissys.demon.co.uk/f7tx2.html"/>
<reference title="Aerodynamic Design of Transport Aircraft
http://www.scribd.com/doc/23956816/Aerodynamic-Design-of-Transport-Aircraft"/>
<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. This model is not
to be sold.
</note>
</fileheader>
<!--
File: Fokker-100.xml
Inputs:
name: Fokker-100
type: two-engine transonic transport
max weight: 95013.45 lb
wing span: 92.13048 ft
length: 106.6325 ft
wing area: 1006.5275 sq-ft
gear type: tricycle
retractable?: yes
# engines: 2
engine type: turbine
engine layout: aft fuselage
yaw damper? yes
Outputs:
wing loading: 94.40 lb/sq-ft
CL-alpha: 4.4 per radian
CL-0: 0.2
CL-max: 1.72
CD-0: 0.02
K: 0.043
-->
<metrics>
<wingarea unit="FT2"> 1006.53 </wingarea>
<wingspan unit="FT" > 92.13 </wingspan>
<wing_incidence> 2.00 </wing_incidence>
<chord unit="FT" > 12.4671 </chord>
<htailarea unit="FT2"> 233.792 </htailarea>
<htailarm unit="FT" > 52.4934 </htailarm>
<vtailarea unit="FT2"> 132.396 </vtailarea>
<vtailarm unit="FT" > 44.6194 </vtailarm>
<location name="AERORP" unit="IN">
<x> 699.48 </x> <!-- 668.48 -->
<y> 0.00 </y>
<z> 38.00 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 122.04 </x>
<y> -30.00 </y>
<z> 88.94 </z>
</location>
<location name="VRP" unit="IN">
<x> 101.65 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 234805 </ixx>
<iyy unit="SLUG*FT2"> 726720 </iyy>
<izz unit="SLUG*FT2"> 925012 </izz>
<emptywt unit="LBS" > 54217 </emptywt>
<location name="CG" unit="IN">
<x> 719.81 </x> <!-- 693.81 -->
<y> 0.00 </y>
<z> 38.12 </z>
</location>
<pointmass name="pilot">
<weight unit="LBS"> 230 </weight>
<location name="POINTMASS" unit="IN">
<x> 122.04 </x>
<y> -30.0 </y>
<z> 66.0 </z>
</location>
</pointmass>
<pointmass name="copilot">
<weight unit="LBS"> 230 </weight>
<location name="POINTMASS" unit="IN">
<x> 122.04 </x>
<y> 30.0 </y>
<z> 66.0 </z>
</location>
</pointmass>
<pointmass name="steward">
<weight unit="LBS"> 400 </weight>
<location name="POINTMASS" unit="IN">
<x> 218 </x>
<y> 32.0 </y>
<z> 66.0 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> 172.87 </x>
<y> 0.00 </y>
<z> -55.73 </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"> 7750.03 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600.34 </damping_coeff>
<max_steer unit="DEG"> 5.00 </max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x> 731.93 </x>
<y>-101.65 </y>
<z> -63.53 </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"> 95013.45 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x> 731.93 </x>
<y> 101.65 </y>
<z> -63.53 </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"> 95013.45 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x> 753.77 </x>
<y>-1105.4 </y>
<z> 0.0 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 95013.45 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x> 753.77 </x>
<y> 1105.4 </y>
<z> 0.0 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 95013.45 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 19002.69 </damping_coeff>
</contact>
</ground_reactions>
<external_reactions>
<force name="pushback" frame="BODY">
<location unit="IN">
<x>-139</x>
<y>0</y>
<z>-71</z>
</location>
<direction>
<x>1</x>
<y>0</y>
<z>0</z>
</direction>
</force>
</external_reactions>
<propulsion>
<engine file="Tay-620">
<location unit="IN">
<x> 922.52 </x>
<y> -101.65 </y>
<z> 43.53 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>0</feed>
<thruster file="direct">
<location unit="IN">
<x> 922.52 </x>
<y> -101.65 </y>
<z> 43.53 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<engine file="Tay-620">
<location unit="IN">
<x> 922.52 </x>
<y> 101.65 </y>
<z> 43.53 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>1</feed>
<thruster file="direct">
<location unit="IN">
<x> 922.52 </x>
<y> 101.65 </y>
<z> 43.53 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL" number="0">
<location unit="IN">
<x> 713.81 </x>
<y>-190.59 </y>
<z> 0.0 </z>
</location>
<capacity unit="LBS"> 13360.01 </capacity>
<contents unit="LBS"> 8688.50 </contents>
</tank>
<tank type="FUEL" number="1">
<location unit="IN">
<x> 713.81 </x>
<y> 190.59 </y>
<z> 0.0 </z>
</location>
<capacity unit="LBS"> 13360.01 </capacity>
<contents unit="LBS"> 8688.50 </contents>
</tank>
<!--
<tank type="FUEL" number="2">
<location unit="IN">
<x> 703.77 </x>
<y> 0.00 </y>
<z> -31.99 </z>
</location>
<capacity unit="LBS"> 1377.01 </capacity>
<contents unit="LBS"> 688.50 </contents>
</tank>
-->
</propulsion>
<system file="pushback"/>
<flight_control name="FCS: Fokker-100">
<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> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="fcs/elevator-normalization">
<input>fcs/elevator-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/elevator-pos-norm</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> -0.35 </min>
<max> 0.35 </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> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="fcs/left-aileron-normalization">
<input>fcs/left-aileron-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="fcs/right-aileron-normalization">
<input>fcs/right-aileron-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </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="fcs/rudder-command-sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min> -0.35 </min>
<max> 0.35 </max>
</clipto>
</summer>
<scheduled_gain name="fcs/yaw-damper-rate">
<input>velocities/r-aero-rad_sec</input>
<table>
<independentVar lookup="row">velocities/ve-kts</independentVar>
<tableData>
30 0.00
60 2.00
</tableData>
</table>
</scheduled_gain>
<scheduled_gain name="fcs/yaw-damper-beta">
<input>aero/beta-rad</input>
<table>
<independentVar lookup="row">velocities/ve-kts</independentVar>
<tableData>
30 0.00
60 0.00
</tableData>
</table>
</scheduled_gain>
<summer name="fcs/yaw-damper-sum">
<input>fcs/yaw-damper-beta</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min> -0.1 </min>
<max> 0.1 </max>
</clipto>
</summer>
<scheduled_gain name="fcs/yaw-damper-final">
<input>fcs/yaw-damper-sum</input>
<table>
<independentVar lookup="row">velocities/ve-kts</independentVar>
<tableData>
30 0.0
31 1.0
</tableData>
</table>
</scheduled_gain>
<summer name="fcs/rudder-sum">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-final</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="fcs/rudder-control">
<input>fcs/rudder-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="rcs/rudder-normalization">
<input>fcs/rudder-pos-rad</input>
<domain>
<min> -0.35 </min>
<max> 0.35 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/rudder-pos-norm</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>8</position>
<time>3</time>
</setting>
<setting>
<position>15</position>
<time>3</time>
</setting>
<setting>
<position>25</position>
<time>4</time>
</setting>
<setting>
<position>42</position>
<time>4</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="fcs/flap-normalization">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min>
<max>42</max>
</domain>
<range>
<min>0</min>
<max>1</max>
</range>
<output>fcs/flap-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Landing Gear">
<kinematic name="fcs/gear-control">
<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>
</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="Spoilers">
<kinematic name="fcs/spoiler-control">
<input>fcs/spoiler-cmd-norm</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>1</position>
<time>1</time>
</setting>
</traverse>
<output>fcs/spoiler-pos-norm</output>
</kinematic>
</channel>
</flight_control>
<aerodynamics>
<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 0.0350
0.1000 0.4170
0.1500 0.5390
0.2000 0.6240
0.3000 0.7510
0.4000 0.8000
0.5000 0.8960
0.6000 0.9390
0.7000 0.9740
0.8000 0.9810
0.9000 0.9900
1.0000 0.9940
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 1.3910
0.1000 1.2350
0.1500 1.1670
0.2000 1.1350
0.3000 1.0850
0.4000 1.1020
0.5000 1.0350
0.6000 1.0240
0.7000 1.0150
0.8000 1.0110
0.9000 1.0060
1.0000 1.0040
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<function name="aero/function/kCmge">
<description>Change_in_pitch_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>
<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>
<property>aero/function/kCDge</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-1.5700 1.5000
-0.2600 0.0400
0.0000 0.01922
0.2600 0.0400
1.5700 1.5000
</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/function/kCDge</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.458 0.04432
0.546 0.02207
0.600 0.01469
0.720 0.00867
0.800 0.00478
0.860 0.00358
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDDflap">
<description>Drag_due_to_flap_deflection</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>
0.000 25.0 42.0
-0.07 0.0000 0.0047 0.0156
0.00 0.0000 0.0070 0.0200
0.03 0.0001 0.0077 0.0225
0.07 0.0005 0.0089 0.0257
0.10 0.0008 0.0129 0.0276
0.14 0.0025 0.0156 0.0313
</tableData>
</table>
</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>
0.000 0.00000
0.600 0.00000
0.650 0.00026
0.720 0.00115
0.770 0.00251
0.800 0.00373
0.848 0.01067
0.860 0.01858
1.000 0.02737
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDgear">
<description>Drag_due_to_gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.0120</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>0.1200</value>
</product>
</function>
<function name="aero/coefficient/CDsp">
<description>Drag_due_to_spoilers</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/spoiler-pos-norm</property>
<value>0.0280</value>
</product>
</function>
<function name="aero/coefficient/CDrv">
<description>Drag_due_to_reverse</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>propulsion/engine[0]/reverser-angle-rad</property>
<property>propulsion/engine[1]/reverser-angle-rad</property>
<value>0.0187</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/beta-rad</independentVar>
<tableData>
-1.5700 1.2300
-0.2600 0.0500
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/mag-elevator-pos-rad</property>
<value>0.0590</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>-1.0000</value>
</product>
</function>
</axis>
<axis name="LIFT">
<function name="aero/coefficient/CLflaps">
<description>Lift_due_to_flap_deflection</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">fcs/flap-pos-deg</independentVar>
<tableData>
0.000 25.0 42.0
0.00 0.217 0.837 1.269
0.17 1.109 1.701 2.173
0.21 1.270 1.827 2.308
0.24 1.400 1.722 1.908
0.28 1.336 0.707 0.000
0.60 0.600 0.000 0.000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLsp">
<description>Delta_Lift_due_to_spoiler</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/spoiler-pos-norm</property>
<property>aero/function/kCLge</property>
<value>-0.1200</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>0.2000</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<value>-0.1000</value>
</product>
</function>
<function name="aero/coefficient/Clp">
<description>Roll_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>-0.4000</value>
</product>
</function>
<function name="aero/coefficient/Clr">
<description>Roll_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>0.1500</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>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<independentVar lookup="column">fcs/left-aileron-pos-rad</independentVar>
<tableData>
-0.349 -0.1745 0.000 0.1745 0.349
0.00 -0.043 -0.022 0.000 0.022 0.043
0.60 -0.043 -0.022 0.000 0.022 0.043
0.65 -0.037 -0.022 0.000 0.022 0.037
0.70 -0.027 -0.022 0.000 0.023 0.027
0.75 -0.027 -0.019 0.000 0.019 0.027
0.88 -0.026 -0.019 0.000 0.019 0.026
</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>0.0100</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>
<property>aero/function/kCmge</property>
<value>-0.000737</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>
<property>aero/alpha-rad</property>
<value>-0.6000</value>
</product>
</function>
<function name="aero/coefficient/Cmde">
<description>Pitch_moment_due_to_elevator</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 -1.2000
2.0000 -0.3000
</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>-31.0000</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>-16.0000</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>
<value>0.1200</value>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value>-0.1500</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>-0.1000</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>0.0000</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>