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: 1.3 $</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"/>
</fileheader>
<!--
File: xf100.xml
Inputs:
name: NG-Aircraft XF-100 (Fokker 100NG)
type: two-engine transonic transport
max weight: 95013.45 lb
wing span: 92.13048 ft
length: 106.6325 ft
wing area: 1025.9045 sq-ft
gear type: tricycle
retractable?: yes
# engines: 2
engine type: turbine
engine layout: aft fuselage
yaw damper? yes
Outputs:
wing loading: 83.35 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"> 1025.90 </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"> 218368 </ixx>
<iyy unit="SLUG*FT2"> 675849 </iyy>
<izz unit="SLUG*FT2"> 860261 </izz>
<emptywt unit="LBS" > 51307 </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="BR-725">
<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="BR-725">
<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"> 688.50 </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"> 688.50 </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>
<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 0.0392
0.0000 0.01884
0.2600 0.0392
1.5700 1.4700
</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>
<property>aero/function/kCDge</property>
<value>0.00717</value>
</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>
<property>aero/function/kCDge</property>
<value>0.0830</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
0.6500 0.0000
0.7700 0.0015
0.8600 0.0200
1.1000 0.0390
1.8000 0.0260
</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/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.20 -0.680
0.00 0.221
0.23 1.300
0.60 0.612
</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>
<property>aero/function/kCLge</property>
<table>
<independentVar>fcs/flap-pos-norm</independentVar>
<tableData>
0.0000 0.0000
0.3570 0.4900
1.0000 1.1800
</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>
<property>fcs/left-aileron-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.1000
2.0000 0.0330
</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/function/kCmge">
<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/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>