jsbsim.js
Version:
JSBSim flight dynamics model ported to JavaScript
931 lines (884 loc) • 36.8 kB
text/xml
<fdm_config name="fokker50" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> External model, animations and FDM by Erik Hofman. Cockpit model in progress, work by the FlightGear community. </author>
<filecreationdate> In progress January 2008 </filecreationdate>
<version> External model $Revision: 1.21 $ Cockpit model in development.</version>
<author> Erik Hofman </author>
<filecreationdate> 2002-01-01</filecreationdate>
<version> $Revision: 1.21 $ </version>
<description> Fokker 50 commercial turboprop airliner </description>
<reference refID="None" author="n/a" title="n/a" date="n/a"/>
<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>
<metrics>
<wingarea unit="FT2"> 753.55 </wingarea>
<wingspan unit="FT"> 95.15 </wingspan>
<chord unit="FT"> 7.92 </chord>
<htailarea unit="FT2"> 120.57 </htailarea>
<htailarm unit="FT"> 41.42 </htailarm>
<vtailarea unit="FT2"> 135.64 </vtailarea>
<vtailarm unit="FT"> 41.42 </vtailarm>
<location name="AERORP" unit="IN">
<x> 497.1 </x> <!--491.1-->
<y> 0 </y>
<z> 0 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 0 </x> <!-- 79.5 -->
<y> 0 </y> <!-- Original -24 -->
<z> 0 </z> <!--original 65 -->
</location>
<location name="VRP" unit="IN">
<x> 497.1 </x> <!-- 497.1 -->
<y> 0 </y>
<z> -24.9 </z> <!-- original -24.9 -->
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 474936 </ixx>
<iyy unit="SLUG*FT2"> 430723 </iyy>
<izz unit="SLUG*FT2"> 896344 </izz>
<emptywt unit="LBS"> 29700 </emptywt>
<location name="CG" unit="IN">
<x> 497.1 </x>
<y> 0 </y>
<z> -24.9 </z>
</location>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> 129.2 </x>
<y> 0 </y>
<z> -119.3 </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"> 13196.9 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4399 </damping_coeff>
<max_steer unit="DEG"> 65 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MLG">
<location unit="IN">
<x> 521.9 </x>
<y> -125.6 </y>
<z> -119.3 </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"> 43989.8 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 8798 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MLG">
<location unit="IN">
<x> 521.9 </x>
<y> 125.6 </y>
<z> -119.3 </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"> 43989.8 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 8798 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="RWT">
<location unit="IN">
<x> 497.1 </x>
<y> 47.575 </y>
<z> -24.9 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="LWT">
<location unit="IN">
<x> 497.1 </x>
<y> -47.575 </y>
<z> -24.9 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x> 994.143 </x>
<y> 0 </y>
<z> -24.9 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="BELLY">
<location unit="IN">
<x> 497.1 </x>
<y> 0 </y>
<z> -49.8 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<contact type="STRUCTURE" name="VTT">
<location unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 303.1 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<rolling_friction> 0.2 </rolling_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<!-- <engine file="PWC125B_Aeromatic"> -->
<engine file="PW125BX">
<location unit="IN">
<x> 497.072 </x>
<y> -190.298 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<thruster file="dowty-rotol-aero">
<!-- <thruster file="prop_RAF-6-mod"> -->
<!-- <thruster file="direct"> -->
<location unit="IN">
<x> 497.072 </x>
<y> -190.298 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<!-- <engine file="PWC125B_Aeromatic"> -->
<engine file="PW125BX">
<location unit="IN">
<x> 497.072 </x>
<y> 190.298 </y>
<z> -40 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>1</feed>
<thruster file="dowty-rotol-aero">
<!-- <thruster file="prop_RAF-6-mod"> -->
<!-- <thruster file="direct"> -->
<location unit="IN">
<x> 497.072 </x>
<y> 190.298 </y>
<z> -40 </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> 497.072 </x>
<y> 3 </y>
<z> -24.8536 </z>
</location>
<capacity unit="LBS"> 4576 </capacity>
<contents unit="LBS"> 1100 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 1 -->
<location unit="IN">
<x> 497.072 </x>
<y> -3 </y>
<z> -24.8536 </z>
</location>
<capacity unit="LBS"> 4576 </capacity>
<contents unit="LBS"> 1100 </contents>
</tank> <!--
<tank type="FUEL"> Tank number 2
<location unit="IN">
<x> 497.072 </x>
<y> 0 </y>
<z> -24.8536 </z>
</location>
<capacity unit="LBS"> 814.6 </capacity>
<contents unit="LBS"> 407.3 </contents>
</tank> -->
</propulsion>
<flight_control name="Fokker50">
<channel name="EEC">
<switch name="fcs/eec-throttle-multiplier">
<default value="0.825"/>
<test logic="AND" value="1.0"> <!-- GA == 1 -->
/systems/fokker50/erp/settingn GT 0.5
/systems/fokker50/erp/settingn LT 1.5
</test>
<test logic="AND" value="0.93"> <!-- TO == 2 -->
/systems/fokker50/erp/settingn GT 1.5
/systems/fokker50/erp/settingn LT 2.5
</test>
<test logic="AND" value="0.95"> <!-- MCT == 3 -->
/systems/fokker50/erp/settingn GT 2.5
/systems/fokker50/erp/settingn LT 3.5
</test>
<test logic="AND" value="0.82"> <!-- CRZ == 5 -->
/systems/fokker50/erp/settingn GT 4.5
/systems/fokker50/erp/settingn LT 5.5
</test>
<test logic="AND" value="0.91"> <!-- CLB == 4 -->
/systems/fokker50/erp/settingn GT 3.5
/systems/fokker50/erp/settingn LT 4.5
</test>
</switch>
<fcs_function name="fcs/eec-throttle-pos-norm[0]">
<function>
<product>
<property> fcs/eec-throttle-multiplier </property>
<property> /controls/engines/engine/throttle </property>
</product>
</function>
<output>fcs/throttle-cmd-norm[0]</output>
</fcs_function>
<fcs_function name="fcs/eec-throttle-pos-norm[1]">
<function>
<product>
<property> fcs/eec-throttle-multiplier </property>
<property> /controls/engines/engine[1]/throttle </property>
</product>
</function>
<output>fcs/throttle-cmd-norm[1]</output>
</fcs_function>
<!-- Control Np. GA =1 TO =2 MCT =3 CLB = 4 CRZ =5, plus 0.5 for gnd idle range -->
<switch name="fcs/erp-np-cmd">
<default value="0.825"/>
<test logic="OR" value="0.495">
/systems/fokker50/erp/settinggi == 5
/systems/fokker50/erp/settinggi == 4
</test>
<test logic="OR" value="0">
/systems/fokker50/erp/settinggi == 2.5
/systems/fokker50/erp/settinggi == 3.5
/systems/fokker50/erp/settinggi == 4.5
/systems/fokker50/erp/settinggi == 5.5
</test>
<output>fcs/advance-pos-norm[1]</output>
<output>fcs/advance-pos-norm</output>
</switch>
<switch name="fcs/erp-np-cmd[1]">
<default value="0.825"/>
<test logic="OR" value="0.495">
/systems/fokker50/erp/settinggi == 5
/systems/fokker50/erp/settinggi == 4
</test>
<test logic="OR" value="0">
/systems/fokker50/erp/settinggi == 2.5
/systems/fokker50/erp/settinggi == 3.5
/systems/fokker50/erp/settinggi == 4.5
/systems/fokker50/erp/settinggi == 5.5
</test>
<output>fcs/advance-pos-norm</output>
</switch>
</channel>
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
<output>fcs/elevator-pos-norm</output>
</summer>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<range>
<min>-0.35</min>
<max>0.3</max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
<output>fcs/left-aileron-pos-norm</output>
</summer>
<aerosurface_scale name="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="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>
</channel>
<channel name="Yaw">
<summer name="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>
<scheduled_gain name="Yaw Damper Rate">
<input>velocities/r-aero-rad_sec</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.00 0.00
11.00 2.00
</tableData>
</table>
</scheduled_gain>
<scheduled_gain name="Yaw Damper Beta">
<input>aero/beta-rad</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.00 0.00
11.00 0.00
</tableData>
</table>
</scheduled_gain>
<summer name="Yaw Damper Sum">
<input>fcs/yaw-damper-beta</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min>-0.2</min>
<max>0.2</max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Final">
<input>fcs/yaw-damper-sum</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
2.99 0.00
3.00 1.00
</tableData>
</table>
</scheduled_gain>
<summer name="Rudder Sum">
<input>fcs/rudder-command-sum</input>
<input>fcs/yaw-damper-final</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
<output>fcs/rudder-pos-norm</output>
</summer>
<aerosurface_scale name="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>
</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>0.5</position>
<time>4</time>
</setting>
<setting>
<position>1.0</position>
<time>3</time>
</setting>
</traverse>
<output>fcs/flap-pos-norm</output>
</kinematic>
</channel>
<channel name="Landing Gear">
<kinematic name="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="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>
</flight_control>
<system name="NWS">
<property>systems/NWS/engaged</property>
<channel name="Nose Wheel Steering">
<scheduled_gain name="systems/NWS/steer-cmd">
<input>fcs/rudder-cmd-norm</input>
<table>
<independentVar lookup="row">systems/NWS/engaged</independentVar>
<tableData>
0 -0.1
1 -1.0
</tableData>
</table>
<output>fcs/steer-cmd-norm</output>
</scheduled_gain>
</channel>
</system>
<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 0.0480
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>
<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 1.5000
-0.2600 0.0500
0.0000 0.0250
0.2600 0.0500
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/cl-squared</property>
<property>aero/function/kCDge</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>
<property>aero/function/kCDge</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>
<property>aero/function/kCDge</property>
<value>0.0350</value>
</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>0.0230</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>0.0250</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>
<abs><property>fcs/elevator-pos-norm</property></abs>
<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>-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>
-0.2000 -0.7400
0.0000 0.2400
0.2400 1.4000
0.6000 0.7040
</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>fcs/flap-pos-norm</property>
<property>aero/function/kCLge</property>
<value>0.6000</value>
</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>0.2000</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>-->
<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 0.1500
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>0.0100</value>
</product>
</function>
</axis>
<axis name="PITCH">
<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>-0.4000</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 -1.0000
2.0000 -0.2500
</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>-22.0000</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>-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>
<value>0.1200</value>
<!-- <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>-0.0080</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>