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787-8-GEnx.xml
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787-8-GEnx.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="787-8" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Narendran Muraleedharan, Dwayne Gable and Nicky Ivy</author>
<filecreationdate> 2020-08-08 </filecreationdate>
<version>$Revision: 1.10 $</version>
<description> Flight Dynamics Model for the Boeing 787-8 GEnx. Revised by IskenderWang</description>
</fileheader>
<!-- UNIT CONVERSIONS :
1 meter = 3.2 feet
1 meter = 39.4 inches
1 sq. m = 10.24 sq. ft.
1 feet = 12 inches -->
<metrics>
<wingarea unit="FT2"> 3501.7984 </wingarea> <!-- Wikipedia -->
<wingspan unit="FT"> 192 </wingspan> <!-- Wikipedia -->
<wing_incidence unit="DEG"> 2 </wing_incidence> <!-- From old 787 FDM -->
<chord unit="FT"> 38.94 </chord> <!-- Measured -->
<htailarea unit="FT2"> 343.36 </htailarea> <!-- Calculated on paper -->
<htailarm unit="FT"> 81.6 </htailarm> <!-- Measured -->
<vtailarea unit="FT2"> 471.77728 </vtailarea> <!-- Calculated on paper -->
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<!-- Center of AircrafT (0,0,0 in Ac3D) is taken as the Eyepoint -->
<location name="EYEPOINT" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<!-- Center of Aircraft (in Ac3D) is taken as the Vehicle Reference Point -->
<location name="VRP" unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 7675399.200088156 </ixx> <!-- Values from YASIM Solver (old 787 FDM) -->
<iyy unit="SLUG*FT2"> 6595543.304209171 </iyy> <!-- Values from YASIM Solver (old 787 FDM) -->
<izz unit="SLUG*FT2"> 22197429.613714606 </izz> <!-- Values from YASIM Solver (old 787 FDM) -->
<ixy unit="SLUG*FT2"> 0.015488805 </ixy> <!-- Values from YASIM Solver (old 787 FDM) -->
<ixz unit="SLUG*FT2"> 0.015488805 </ixz> <!-- Values from YASIM Solver (old 787 FDM) -->
<iyz unit="SLUG*FT2"> 0 </iyz>
<emptywt unit="LBS"> 239200 </emptywt> <!-- Supposed to be 242000 but the plane acts too heavy with that setting -->
<location name="CG" unit="IN">
<!-- Values from YASIM Solver (old 787 FDM) -->
<x> -16 </x>
<y> 0.00 </y>
<z>22.5972</z>
</location>
<!--Crew. Min 350 Max 500 Default 350, for two crew members in the
cockpit.-->
<pointmass name="Crew">
<weight unit="LBS">350</weight>
<location name="POINTMASS" unit="IN">
<x>-898.32</x>
<z>51.22</z>
</location>
</pointmass>
<!--First class. 12 seats, adding 360 pounds for 30 pounds of seat
accessories for each seat. Min 360 Max 2160 Default 1800-->
<pointmass name="first-class">
<weight unit="LBS">1800</weight>
<location name="POINTMASS" unit="IN">
<x>-591</x>
<z>78.8</z>
</location>
</pointmass>
<!--Business class. 42 seats. Min 0 Max 7560 Default 6400-->
<pointmass name="business-class">
<weight unit="LBS">6400</weight>
<location name="POINTMASS" unit="IN">
<x>-216.7</x>
<z>78.8</z>
</location>
</pointmass>
<!--Economy class. 170 seats. Min 0 Max 30600 Default 25000-->
<pointmass name="economy-class">
<weight unit="LBS">25000</weight>
<location name="POINTMASS" unit="IN">
<x>157.6</x>
<z>78.8</z>
</location>
</pointmass>
<!--Forward cargo. I don't know how much cargo usually goes on an
average plane flight, so I guessed. Min 0 Max 10000 Default 10000-->
<pointmass name="forward-cargo">
<weight unit="LBS">10000</weight>
<location name="POINTMASS" unit="IN">
<x>-394</x>
<z>-39.4</z>
</location>
</pointmass>
<!--Rear cargo. Same as above, but Min 0 Max 10000 Default 5000-->
<pointmass name="forward-cargo">
<weight unit="LBS">5000</weight>
<location name="POINTMASS" unit="IN">
<x>157.6</x>
<z>-39.4</z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<!-- Nose Gear Contact Point -->
<contact type="BOGEY" name="NOSE_GEAR">
<location unit="IN">
<x> -809.50058 </x>
<y> 0.00 </y>
<z> -143.36872 </z>
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.30 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 160000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 80000 </damping_coeff>
<max_steer unit="DEG"> 70 </max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>
<!-- Left Main Gear Contact Point -->
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x> 77.1058 </x>
<y> -193.59978 </y>
<z> -153.63242 </z>
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.35 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>
<!-- Right Main Gear Contact Point -->
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x> 77.1058 </x>
<y> 193.59978 </y>
<z> -153.63242 </z>
</location>
<static_friction> 0.40 </static_friction>
<dynamic_friction> 0.35 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 833000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 166600 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>
<!-- Left Wing Tip Contact Point -->
<contact type="STRUCTURE" name="LEFT_WING_TIP">
<location unit="IN">
<x> 549.236 </x>
<y> -1173.48172 </y>
<z> 154.83018 </z>
</location>
<static_friction> 0.5 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!-- Right Wing Tip Contact Point -->
<contact type="STRUCTURE" name="RIGHT_WING_TIP">
<location unit="IN">
<x> 549.236 </x>
<y> 1173.48172 </y>
<z> 154.83018 </z>
</location>
<static_friction> 0.5 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!-- Tail (in case of a tail strike) Contact Point -->
<contact type="STRUCTURE" name="TAIL_STRIKE">
<location unit="IN">
<x> 924.93864 </x>
<y> 0 </y>
<z> 3.41992 </z>
</location>
<static_friction> 0.5 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
<!-- Nose (used for Ditching) Contact Point -->
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x> -984.2908 </x>
<y> 0 </y>
<z> -29.8455 </z>
</location>
<static_friction> 0.5 </static_friction>
<dynamic_friction> 0.4 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 100000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 20000 </damping_coeff>
<brake_group> NONE </brake_group>
<retractable>0</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="genx-1b-8">
<location unit="IN">
<x> -211.92078 </x>
<y> -383.15712</y>
<z> -31.29148 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>2</feed>
<feed>0</feed>
<thruster file="direct">
<location unit="IN">
<x> -211.92078 </x>
<y> -383.15712</y>
<z> -31.29148 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<engine file="genx-1b-8">
<location unit="IN">
<x> -211.92078 </x>
<y> 383.15712</y>
<z> -31.29148 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed>1</feed>
<feed>2</feed>
<thruster file="direct">
<location unit="IN">
<x> -211.92078 </x>
<y> 383.15712</y>
<z> -31.29148 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<!-- Wing Fuel Tank LEFT -->
<tank type="FUEL" number="0">
<location unit="IN">
<x> 0 </x>
<y> -295.5 </y>
<z> 25.61 </z>
</location>
<capacity unit="KG"> 23586.80324 </capacity>
<contents unit="KG"> 15000 </contents>
</tank>
<!-- Wing Fuel Tank RIGHT -->
<tank type="FUEL" number="1">
<location unit="IN">
<x> 0 </x>
<y> 295.5 </y>
<z> 25.61 </z>
</location>
<capacity unit="KG"> 23586.80324 </capacity>
<contents unit="KG"> 15000 </contents>
</tank>
<!-- Central Fuel Tank -->
<tank type="FUEL" number="2">
<location unit="IN">
<x> 0.00 </x>
<y> 0.00 </y>
<z> -39.4 </z>
</location>
<capacity unit="KG"> 54431.0844 </capacity>
<contents unit="KG"> 30000 </contents>
</tank>
</propulsion>
<system file="pushback" />
<system file="Defines" />
<flight_control name="FCS: 787-8">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>fcs/elevator-cmd-norm</input>
<input>fcs/pitch-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="Elevator Control">
<input>fcs/pitch-trim-sum</input>
<range>
<min> -0.35 </min>
<max> 0.35 </max>
</range>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="elevator normalization">
<input>fcs/elevator-pos-rad</input>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>fcs/aileron-cmd-norm</input>
<input>fcs/roll-trim-cmd-norm</input>
<clipto>
<min> -1 </min>
<max> 1 </max>
</clipto>
</summer>
<aerosurface_scale name="Left Aileron Control">
<input>fcs/roll-trim-sum</input>
<range>
<min> -0.25 </min>
<max> 0.25 </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> -0.25 </min>
<max> 0.25 </max>
</range>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="left aileron normalization">
<input>fcs/left-aileron-pos-rad</input>
<domain>
<min> -0.25 </min>
<max> 0.25 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="right aileron normalization">
<input>fcs/right-aileron-pos-rad</input>
<domain>
<min> -0.25 </min>
<max> 0.25 </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="Rudder Command Sum">
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min> -0.25 </min>
<max> 0.25 </max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Rate">
<input>velocities/r-aero-rad_sec</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.0000 0.0000
11.0000 2.0000
</tableData>
</table>
</scheduled_gain>
<scheduled_gain name="Yaw Damper Beta">
<input>aero/beta-rad</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
3.0000 0.0000
11.0000 0.0000
</tableData>
</table>
</scheduled_gain>
<summer name="Yaw Damper Sum">
<input>fcs/yaw-damper-beta</input>
<input>fcs/yaw-damper-rate</input>
<clipto>
<min>-0.2000</min>
<max>0.2000</max>
</clipto>
</summer>
<scheduled_gain name="Yaw Damper Final">
<input>fcs/yaw-damper-sum</input>
<table>
<independentVar>aero/qbar-psf</independentVar>
<tableData>
2.9900 0.0000
3.0000 1.0000
</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>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/rudder-sum</input>
<range>
<min> -0.25 </min>
<max> 0.25 </max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="rudder normalization">
<input>fcs/rudder-pos-rad</input>
<domain>
<min> -0.25 </min>
<max> 0.25 </max>
</domain>
<range>
<min> -1 </min>
<max> 1 </max>
</range>
<output>fcs/rudder-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Flaps">
<kinematic name="Flaps Control">
<input>fcs/flap-cmd-norm</input>
<traverse>
<setting>
<position>0.0</position>
<time>0.0000</time>
</setting>
<setting>
<position>35.000</position>
<time>30.0000</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="flap normalization">
<input>fcs/flap-pos-deg</input>
<domain>
<min> 0 </min>
<max> 35 </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="Gear Control">
<input>gear/gear-cmd-norm</input>
<traverse>
<setting>
<position> 0 </position>
<time> 0 </time>
</setting>
<setting>
<position> 1 </position>
<time> 15 </time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
</channel>
<!-- Nose wheel steering gets input from Systems/ground_steering.xml -->
<channel name="Steering">
<fcs_function name="Nose Wheel Steering 0">
<function name="fcs/steer-nose-deg[0]">
<description>Steering command for nose gear</description>
<product>
<property>/controls/gear/steering-cmd-norm</property>
<value>70.0</value>
</product>
</function>
</fcs_function>
<actuator name="Gear Nose Actuator">
<input>fcs/steer-nose-deg[0]</input>
<rate_limit>70</rate_limit>
<output>fcs/steer-pos-deg[0]</output>
</actuator>
</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> 2 </time>
</setting>
</traverse>
<output>fcs/speedbrake-pos-norm</output>
</kinematic>
</channel>
</flight_control>
<aerodynamics>
<!-- Lift due to ground effects -->
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<product>
<value>1.0</value>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 1.1523
0.1000 1.0961
0.1500 1.0551
0.2000 1.0439
0.3000 1.0327
0.4000 1.0268
0.5000 1.0143
0.6000 1.0101
0.7000 1.0060
0.8000 1.0048
0.9000 1.0024
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<!-- Drag due to ground effects -->
<function name="aero/function/kCDge">
<description>Change_in_drag_due_to_ground_effect</description>
<product>
<value>1.0</value>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 0.6100
0.1000 0.6363
0.1500 0.7218
0.2000 0.7818
0.3000 0.8613
0.4000 0.9115
0.5000 0.9460
0.6000 0.9715
0.7000 0.9910
0.8000 0.9955
0.9000 1.0000
1.0000 1.0000
</tableData>
</table>
</product>
</function>
<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>/controls/ice/wing/lift-coefficient</property>
<property>aero/function/kCLge</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<!-- <independentVar lookup="column">/velocities/mach</independentVar> -->
<tableData>
-0.2000 -0.8000
0.0000 0.3400
0.0400 0.5700
0.1740 1.0054
0.3000 1.3400
0.4500 1.2500
0.6000 0.8000
</tableData>
<!-- <tableData> Devel > CLalpha/Graph 4
-0.5230 -0.6000
0.0000 0.4000
0.0500 0.5000
0.1000 0.6000
0.5000 1.4000
</tableData> -->
<!-- <tableData> Devel > CLalpha/Graph 3
-0.5230 -0.8000
-0.4000 -0.6000
-0.3000 -0.4000
-0.2000 -0.2000
-0.1000 0.0000
-0.0500 0.1000
0.0000 0.2000
0.0500 0.3300
0.1000 0.4600
0.2000 0.7000
0.3000 1.0000
0.4000 1.3700
0.5000 2.0000
</tableData> -->
<!-- <tableData> Devel > CLalpha/Graph 2
-0.5230 -0.8000
-0.4000 -0.7500
-0.3000 -0.6700
-0.2000 -0.5500
-0.1000 -0.2600
-0.0600 0.0000
-0.0423 0.1500
0.0000 0.4000
0.0523 0.6500
0.1745 1.1200
0.2617 1.3000
0.4000 1.3000
0.5000 1.0500
0.5500 0.8000
0.6000 0.4000
</tableData> -->
<!-- <tableData> Devel > CLalpha/Graph 1
-0.2000 -0.6800
0.0000 0.2000
0.0400 0.6400
0.2300 2.7000
0.6000 0.5000
</tableData> -->
</table>
</product>
</function>
<function name="aero/force/Lift_flap">
<description>Delta Lift due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.024 </value>
</product>
</function>
<function name="aero/force/Lift_speedbrake">
<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>-0.2</value>
</product>
</function>
<function name="aero/force/Lift_elevator">
<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>0.55</value>
</product>
</function>
</axis>
<axis name="DRAG">
<function name="aero/force/Drag_basic">
<description>Drag at zero lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>/controls/ice/wing/drag-coefficient</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-1.57 1.400
-0.26 0.020
0.00 0.015
0.26 0.026
1.57 1.600
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_induced">
<description>Induced drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<property>/controls/ice/wing/drag-coefficient</property>
<property>aero/function/kCDge</property>
<value>0.04</value>
</product>
</function>
<function name="aero/force/Drag_mach">
<description>Drag due to mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>/controls/ice/wing/drag-coefficient</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.00 0.000
0.79 0.001
1.10 0.043
1.80 0.055
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_flap">
<description>Drag due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<property>aero/function/kCDge</property>
<value> 0.0025 </value>
</product>
</function>
<function name="aero/force/Drag_gear">
<description>Drag due to gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value>0.0035</value>
</product>
</function>
<function name="aero/force/Drag_speedbrake">
<description>Drag due to speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.07</value>
</product>
</function>
<function name="aero/force/Drag_beta">
<description>Drag due to sideslip</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<tableData>
-1.57 1.230
-0.26 0.050
0.00 0.000
0.26 0.050
1.57 1.230
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_elevator">
<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>0.025</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/force/Side_beta">
<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</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/moment/Roll_beta">
<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>-0.08</value>
</product>
</function>
<function name="aero/moment/Roll_damp">
<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>-0.4</value>
</product>
</function>
<function name="aero/moment/Roll_yaw">
<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>0.15</value>
</product>
</function>
<function name="aero/moment/Roll_aileron">
<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 lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.100
2.0 0.033
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_rudder">
<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>0.01</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/moment/Pitch_alpha">
<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>-1.4</value>
</product>
</function>
<function name="aero/moment/Pitch_elevator">
<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 lookup="row">velocities/mach</independentVar>
<tableData>
0.0000 -1.3000
2.0000 -0.3200
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_damp">
<description>Pitch moment due to pitch rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/ci2vel</property>
<property>velocities/q-aero-rad_sec</property>
<value>-12</value>
</product>
</function>
<function name="aero/moment/Pitch_alphadot">
<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>