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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
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<fdm_config name= "A320family" version= "2.0" release= "BETA"
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xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader >
<author > Bicyus (Jon Ortuondo) </author>
<email > bicyus@gmail.com </email>
<filecreationdate > 2012-02-15 </filecreationdate>
<version > 0.99 </version>
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<description > Airbus A320-200 with IAE V2500 Engines </description>
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<note > Fork from the A320-Family aircraft project (Thanks to all authors) </note>
<limitation > </limitation>
</fileheader>
<metrics >
<wingarea unit= "FT2" > 1319.79 </wingarea>
<wingspan unit= "FT" > 111.26 </wingspan>
<wing_incidence > 1.03 </wing_incidence>
<chord unit= "FT" > 13.76 </chord>
<htailarea unit= "FT2" > 334.24 </htailarea>
<htailarm unit= "FT" > 57.88 </htailarm>
<vtailarea unit= "FT2" > 248.79 </vtailarea>
<vtailarm unit= "FT" > 57.33 </vtailarm>
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<!-- location name="AERORP" unit="IN">
<x > 642.122 </x>
<y > 0 </y>
<z > -25.2091 </z>
< /location -->
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<location name= "AERORP" unit= "IN" >
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<x > 680.00 </x>
<y > 0 </y>
<z > 0.00 </z>
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</location>
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<location name= "EYEPOINT" unit= "IN" >
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<x > 80 </x>
<y > -30 </y>
<z > 70 </z>
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</location>
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<location name= "VRP" unit= "IN" >
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<x > 661.1 </x>
<y > 0 </y>
<z > -37 </z>
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</location>
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</metrics>
<mass_balance >
<ixx unit= "SLUG*FT2" > 611903 </ixx>
<iyy unit= "SLUG*FT2" > 1735389 </iyy>
<izz unit= "SLUG*FT2" > 2301293 </izz>
<!--
___________________A320_________A330__________A340
BOW_____________178000________270000________283925
SPAN______________144___________198___________209
LENGTH____________153___________209___________209
ROLL MOI_________1725000______5727777_______10613448
PITCH MOI________2550000______19040141_______13904249
YAW MOI_________3950000______23089847_______24848934
<ixx unit= "SLUG*FT2" > 2262183 </ixx>
<iyy unit= "SLUG*FT2" > 3172439 </iyy>
<izz unit= "SLUG*FT2" > 3337024 </izz>
<ixx unit= "SLUG*FT2" > 1725000</ixx>
<iyy unit= "SLUG*FT2" > 2550000</iyy>
<izz unit= "SLUG*FT2" > 3950000</izz> -->
<ixy unit= "SLUG*FT2" > 0 </ixy>
<ixz unit= "SLUG*FT2" > 0 </ixz>
<iyz unit= "SLUG*FT2" > 0 </iyz>
<emptywt unit= "LBS" > 80431</emptywt> <!-- #ref - 1 page 67, WV016. 90927lbs - 5248x2 (engines)=80431lbs -->
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<!-- #### PB: That makes no sense, the whole aircraft is 1479.1339 inches long. 650inches eqauls to about 43.95% MAC with the Airbus limits according to the AMM between 45% and 49%
Also: The z-axis is -41.73 inches under the zero line of the plane while the pressure point is only -25,91 under the same line and slightly ahead, that causes the plane to behave quite unstable
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-->
<!-- location name="CG" unit="IN">
<! - -x> 642.122 < /x- - >
<x > 650.122 </x> <! - - At zero load of fuel and cargo/pax the CG goes to 642 - - >
<y > 0 </y>
<z > -41.7398 </z>
< /location -->
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<location name= "CG" unit= "IN" >
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<x > 655.00 </x>
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<y > 0 </y>
<z > 0.00 </z>
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</location>
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<pointmass name= "Cockpit Crew" >
<weight unit= "LBS" > 400</weight> <!-- MAX: 400lbs, two pilots -->
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<location name= "POINTMASS" unit= "IN" >
<x > 200</x>
<y > 0</y>
<z > 0</z>
</location>
</pointmass>
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<pointmass name= "Cabin Crew" >
<weight unit= "LBS" > 600</weight> <!-- MAX: 1320lbs, up to six flight - attendants -->
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<location name= "POINTMASS" unit= "IN" >
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<x > 696</x>
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<y > 0</y>
<z > 0</z>
</location>
</pointmass>
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<pointmass name= "PAX 0A (60 seats)" >
<weight unit= "LBS" > 6600</weight> <!-- MAX: 13200lbs, 60 seats -->
<location name= "POINTMASS" unit= "IN" >
<x > 450.1711</x>
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<y > 0</y>
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<z > 0</z>
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</location>
</pointmass>
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<pointmass name= "PAX 0B (60 seats)" >
<weight unit= "LBS" > 6600</weight> <!-- MAX: 13200lbs, 60 seats -->
<location name= "POINTMASS" unit= "IN" >
<x > 739.5669</x>
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<y > 0</y>
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<z > 0</z>
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</location>
</pointmass>
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<pointmass name= "PAX 0C (54 seats)" >
<weight unit= "LBS" > 5940</weight> <!-- MAX: 11880lbs, 54 seats -->
<location name= "POINTMASS" unit= "IN" >
<x > 1093.2729</x>
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<y > 0</y>
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<z > 0</z>
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</location>
</pointmass>
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<pointmass name= "Cargo Hold 1" >
<weight unit= "LBS" > 2000</weight> <!-- MAX: 7500.126lbs -->
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<location name= "POINTMASS" unit= "IN" >
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<x > 383.4792</x>
<y > 0</y>
<z > -29.5</z> <!-- 1.5m and now half of it for the center point of the load -->
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</location>
</pointmass>
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<!-- Cargo Hold 2 doesn't exist, that is the center tank -->
<pointmass name= "Cargo Hold 3" >
<weight unit= "LBS" > 2000</weight> <!-- MAX: 5384.414lbs -->
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<location name= "POINTMASS" unit= "IN" >
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<x > 849.1324</x>
<y > 0</y>
<z > -29.5</z>
</location>
</pointmass>
<pointmass name= "Cargo Hold 4" >
<weight unit= "LBS" > 1500</weight> <!-- MAX: 4651.754lbs -->
<location name= "POINTMASS" unit= "IN" >
<x > 931.0653</x>
<y > 0</y>
<z > -29.5</z>
</location>
</pointmass>
<pointmass name= "Cargo Hold 5" >
<weight unit= "LBS" > 2000</weight> <!-- MAX: 3300.320lbs -->
<location name= "POINTMASS" unit= "IN" >
<x > 1068.2634</x>
<y > 0</y>
<z > 0</z> <!-- Cargo Hold #5 sits higher on the range of the cabin deck, it's only loadable with lifter -->
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</location>
</pointmass>
</mass_balance>
<ground_reactions >
<!-- REF - 1 page 165 + 271 -->
<contact type= "BOGEY" name= "NOSE_LG" >
<location unit= "IN" >
<x > 197.6772 </x>
<y > 0 </y>
<z > -137.9617 </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" > 30935.5 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 16978.5 </damping_coeff>
<max_steer unit= "DEG" > 70 </max_steer> <!-- REF - 1 page 133 -->
<brake_group > NONE </brake_group>
<retractable > 1</retractable>
</contact>
<contact type= "BOGEY" name= "LEFT_MLG" >
<location unit= "IN" >
<!-- <x> 699.9243 </x> -->
<x > 695.3149 </x>
<y > -149.4094 </y>
<z > -150.4824 </z>
</location>
<!-- <static_friction> 0.5 </static_friction> WHAT??? less static than dinamyc friction? -->
<static_friction > 0.8 </static_friction>
<dynamic_friction > 0.5 </dynamic_friction>
<rolling_friction > 0.02 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 59785 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 23957 </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> 697.3425 </x> It should be right left simetric
<x > 699.9243 </x> -->
<x > 695.3149 </x>
<y > 149.4094 </y>
<z > -150.4824 </z>
</location>
<!-- <static_friction> 0.5 </static_friction> WHAT??? less static than dinamyc friction? -->
<static_friction > 0.8 </static_friction>
<dynamic_friction > 0.5 </dynamic_friction>
<rolling_friction > 0.02 </rolling_friction>
<!-- spring_coeff unit="LBS/FT"> 169785 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 33957 </damping_coeff-->
<spring_coeff unit= "LBS/FT" > 59785 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 23957 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > RIGHT </brake_group>
<retractable > 1</retractable>
</contact>
<contact type= "STRUCTURE" name= "NOSE_1" >
<location unit= "IN" >
<x > 37.7953 </x>
<y > 0 </y>
<z > -38.1374 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "NOSE_2" >
<location unit= "IN" >
<x > 128.1102 </x>
<y > 0 </y>
<z > -55.0271 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "CENTER_1" >
<location unit= "IN" >
<x > 274.0157 </x>
<y > 0 </y>
<z > -60.0665 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "CENTER_2" >
<location unit= "IN" >
<x > 930 </x>
<y > 0 </y>
<z > -60.0665 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "ENG_1" >
<location unit= "IN" >
<x > 589.735</x>
<y > -226.575</y>
<z > -95.567</z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "ENG_2" >
<location unit= "IN" >
<x > 589.735</x>
<y > 226.575</y>
<z > -95.567</z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.5 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "TAIL_1" >
<location unit= "IN" >
<x > 1097.9921 </x>
<y > 0 </y>
<z > -44.7722 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "TAIL_2" >
<location unit= "IN" >
<x > 1225 </x>
<y > 0 </y>
<z > -18.8067 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "TAIL_3" >
<location unit= "IN" >
<x > 1341.6142 </x>
<y > 0 </y>
<z > -10.2599 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "TAIL_4" >
<location unit= "IN" >
<x > 1469.0945 </x>
<y > 0 </y>
<z > 47.4138 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 1 </dynamic_friction>
<rolling_friction > 1 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "WING_TIP_1" >
<location unit= "IN" >
<x > 838.8898 </x>
<y > -667.5197 </y>
<z > 35.7926 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 0.4 </dynamic_friction>
<rolling_friction > 0.4 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
<contact type= "STRUCTURE" name= "WING_TIP_2" >
<location unit= "IN" >
<x > 838.8898 </x>
<y > 667.5197 </y>
<z > 35.7926 </z>
</location>
<static_friction > 1.0 </static_friction>
<dynamic_friction > 1 </dynamic_friction>
<rolling_friction > 1 </rolling_friction>
<spring_coeff unit= "LBS/FT" > 50000 </spring_coeff>
<damping_coeff unit= "LBS/FT/SEC" > 50000 </damping_coeff>
<max_steer unit= "DEG" > 0.0 </max_steer>
<brake_group > NONE </brake_group>
<retractable > 0</retractable>
</contact>
</ground_reactions>
<propulsion >
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<engine file= "v2527_a5" >
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<location unit= "IN" >
<x > 589.735 </x>
<y > -226.575 </y>
<z > -45.567 </z>
</location>
<orient unit= "DEG" >
<roll > 0.0 </roll>
<pitch > 2.2 </pitch>
<yaw > 1 </yaw>
</orient>
<feed > 3</feed>
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<feed > 1</feed>
<feed > 2</feed>
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<thruster file= "direct" >
<location unit= "IN" >
<x > 589.735 </x>
<y > -226.575 </y>
<z > -45.567 </z>
</location>
<orient unit= "DEG" >
<roll > 0.0 </roll>
<pitch > 2.2 </pitch>
<yaw > 1 </yaw>
</orient>
</thruster>
</engine>
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<engine file= "v2527_a5" >
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<location unit= "IN" >
<x > 589.735 </x>
<y > 226.575 </y>
<z > -45.567 </z>
</location>
<orient unit= "DEG" >
<roll > 0.0 </roll>
<pitch > 2.2 </pitch>
<yaw > -1 </yaw>
</orient>
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<feed > 3</feed>
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<feed > 5</feed>
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<feed > 4</feed>
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<thruster file= "direct" >
<location unit= "IN" >
<x > 589.735 </x>
<y > 226.575 </y>
<z > -45.567 </z>
</location>
<orient unit= "DEG" >
<roll > 0.0 </roll>
<pitch > 2.2 </pitch>
<yaw > -1 </yaw>
</orient>
</thruster>
</engine>
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<tank type= "FUEL" > <!-- Left Tank (Wing tip Ventilation Surge) 0 -->
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<location unit= "IN" >
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<x > 783.0709 </x>
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<y > -574.4148 </y>
<z > 3.1080 </z>
</location>
<capacity unit= "LBS" > 328.13 </capacity> <!-- need review -->
<contents unit= "LBS" > 0 </contents>
<priority > 4</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
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<tank type= "FUEL" > <!-- Left Tank (Outer) 1 -->
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<location unit= "IN" >
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<x > 739.5669 </x>
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<y > -457.4259 </y>
<z > -8.0898 </z>
</location>
<capacity unit= "LBS" > 1548.8 </capacity> <!-- need review -->
<contents unit= "LBS" > 154.88 </contents>
<standpipe unit= "LBS" > 21</standpipe> <!-- minimun fuel on pipes -->
<priority > 2</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
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<tank type= "FUEL" > <!-- Left Tank (Inner) 2 -->
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<location unit= "IN" >
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<x > 652.5591 </x>
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<y > -236.2992 </y>
<z > -33.9470 </z>
</location>
<capacity unit= "LBS" > 12186.9 </capacity> <!-- need review -->
<contents unit= "LBS" > 2437.38 </contents>
<standpipe unit= "LBS" > 31</standpipe> <!-- minimun fuel on pipes -->
<priority > 3</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
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<tank type= "FUEL" > <!-- Center Tank 3 -->
2016-11-04 22:13:12 +00:00
<location unit= "IN" >
2016-11-08 13:38:48 +00:00
<x > 522.0473 </x>
2016-11-04 22:13:12 +00:00
<y > 0 </y>
<z > -47.0 </z>
</location>
<capacity unit= "LBS" > 14520 </capacity> <!-- need review -->
<contents unit= "LBS" > 0 </contents>
<standpipe unit= "LBS" > 43</standpipe> <!-- minimun fuel on pipes -->
<priority > 1</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
2016-11-06 01:46:53 +00:00
<tank type= "FUEL" > <!-- Right Tank (Inner) 4 -->
2016-11-04 22:13:12 +00:00
<location unit= "IN" >
2016-11-08 13:38:48 +00:00
<x > 652.5591 </x>
2016-11-04 22:13:12 +00:00
<y > 236.2992 </y>
<z > -33.9470 </z>
</location>
<capacity unit= "LBS" > 12186.9 </capacity> <!-- need review -->
<contents unit= "LBS" > 2437.38 </contents>
<standpipe unit= "LBS" > 31</standpipe> <!-- minimun fuel on pipes -->
<priority > 3</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
2016-11-06 01:46:53 +00:00
<tank type= "FUEL" > <!-- Right Tank (Outer) 5 -->
2016-11-04 22:13:12 +00:00
<location unit= "IN" >
2016-11-08 13:38:48 +00:00
<x > 739.5669 </x>
2016-11-04 22:13:12 +00:00
<y > 457.4259 </y>
<z > -8.0898 </z>
</location>
<capacity unit= "LBS" > 1548.8 </capacity> <!-- need review -->
<contents unit= "LBS" > 154.88 </contents>
<standpipe unit= "LBS" > 21</standpipe> <!-- minimun fuel on pipes -->
<priority > 2</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
2016-11-06 01:46:53 +00:00
<tank type= "FUEL" > <!-- Right Tank (Wing tip Ventilation Surge) 6 -->
2016-11-04 22:13:12 +00:00
<location unit= "IN" >
2016-11-08 13:38:48 +00:00
<x > 783.0709 </x>
2016-11-04 22:13:12 +00:00
<y > 574.4148 </y>
<z > 3.1080 </z>
</location>
<capacity unit= "LBS" > 328.13 </capacity> <!-- need review -->
<contents unit= "LBS" > 0 </contents>
<priority > 4</priority>
<type > JET-A1</type>
<temperature > 50</temperature>
</tank>
</propulsion>
<system file= "pushback" />
<!-- system file="a320 - fuel" / -->
<system file= "glass-effect1" />
<flight_control name= "FCS: A320" >
<channel name= "Pitch" >
<summer name= "Pitch Trim Sum" >
<input > /controls/flight/elevator</input>
<input > /controls/flight/elevator-trim</input>
<clipto >
<min > -1</min>
<max > 1</max>
</clipto>
</summer>
<aerosurface_scale name= "Elevator Control" >
<input > fcs/pitch-trim-sum</input>
2016-11-05 04:53:20 +00:00
<gain > 0.025</gain>
2016-11-04 22:13:12 +00:00
<range >
2016-11-05 04:53:20 +00:00
<min > -10</min>
<max > 10</max>
2016-11-04 22:13:12 +00:00
</range>
<output > fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name= "Elevator position normalized" >
<input > fcs/elevator-pos-deg</input>
<domain >
2016-11-05 04:53:20 +00:00
<min > -10</min>
<max > 10</max>
2016-11-04 22:13:12 +00:00
</domain>
<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 > /controls/flight/aileron</input>
<input > /controls/flight/aileron-trim</input>
<clipto >
<min > -1</min>
<max > 1</max>
</clipto>
</summer>
<aerosurface_scale name= "Left Aileron Control" >
<input > fcs/roll-trim-sum</input>
<gain > 0.02</gain>
<range >
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<min > -15</min>
<max > 15</max>
2016-11-04 22:13:12 +00:00
</range>
<output > fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name= "Right Aileron Control" >
<input > -fcs/roll-trim-sum</input>
<gain > 0.02</gain>
<range >
2016-11-05 04:53:20 +00:00
<min > -15</min>
<max > 15</max>
2016-11-04 22:13:12 +00:00
</range>
<output > fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name= "Left Aileron position normalized" >
<input > fcs/left-aileron-pos-deg</input>
<domain >
2016-11-05 04:53:20 +00:00
<min > -15</min>
<max > 15</max>
2016-11-04 22:13:12 +00:00
</domain>
<range >
2016-11-05 04:53:20 +00:00
<min > -1</min>
2016-11-04 22:13:12 +00:00
<max > 1</max>
</range>
<output > fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name= "Right Aileron position normalized" >
<input > fcs/right-aileron-pos-deg</input>
<domain >
2016-11-05 04:53:20 +00:00
<min > -15</min>
<max > 15</max>
2016-11-04 22:13:12 +00:00
</domain>
<range >
2016-11-05 04:53:20 +00:00
<min > -1</min>
2016-11-04 22:13:12 +00:00
<max > 1</max>
</range>
<output > fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
2016-11-05 03:39:28 +00:00
<channel name= "Throttle" >
<pure_gain name= "fcs/throttle1" >
<input > /controls/engines/engine[0]/throttle-fdm</input>
<gain > 1</gain>
<output > fcs/throttle-cmd-norm</output>
<output > fcs/throttle-pos-norm</output>
</pure_gain>
<pure_gain name= "fcs/throttle2" >
<input > /controls/engines/engine[1]/throttle-fdm</input>
<gain > 1</gain>
<output > fcs/throttle-cmd-norm[1]</output>
<output > fcs/throttle-pos-norm[1]</output>
</pure_gain>
</channel>
2016-11-04 22:13:12 +00:00
<channel name= "Yaw" >
<!-- Testing on Ground steering Rudder bug
<pure_gain name= "Yaw Damper Rate" >
<input > velocities/r-rad_sec</input>
<gain > 2</gain>
</pure_gain>
<pure_gain name= "Yaw Damper Beta" >
<input > aero/beta-rad</input>
<gain > -5</gain>
</pure_gain>
<summer name= "Yaw Trim Sum" >
<input > fcs/rudder-cmd-norm</input>
<input > fcs/yaw-trim-cmd-norm</input>
<clipto >
<min > -1</min>
<max > 1</max>
</clipto>
</summer>
<summer name= "Rudder Sum" >
<input > fcs/yaw-trim-sum</input>
<input > fcs/yaw-damper-rate</input>
<input > fcs/yaw-damper-beta</input>
<clipto >
<min > -1</min>
<max > 1</max>
</clipto>
</summer>
<aerosurface_scale name= "Rudder Control" >
<input > fcs/rudder-sum</input>
<gain > 0.01745</gain>
<range >
<min > -25</min>
<max > 25</max>
</range>
<output > fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name= "Rudder position normalized" >
<input > fcs/rudder-pos-deg</input>
<domain >
<min > -25</min>
<max > 25</max>
</domain>
<range >
<min > -1</min>
<max > 1</max>
</range>
<output > fcs/rudder-pos-norm</output>
</aerosurface_scale> -->
<summer name= "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= "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= "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= "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= "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= "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 > -0.35 </min>
<max > 0.35 </max>
</range>
<output > fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name= "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= "Flaps Control" >
<input > fcs/flap-cmd-norm</input>
<traverse >
<setting >
<position > 0</position>
<time > 0</time>
</setting>
<setting >
<position > 40</position>
<time > 40</time>
</setting>
</traverse>
<output > fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name= "Flap position normalized" >
<input > fcs/flap-pos-deg</input>
<domain >
<min > 0</min>
<max > 40</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 > 10</time>
</setting>
</traverse>
<output > gear/gear-pos-norm</output>
</kinematic>
</channel>
<channel name= "Speedbrake" >
<kinematic name= "Speedbrake" >
<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>
<channel name= "Tiller" >
<switch name= "/controls/gear/tiller-disabled" >
<default value= "0" />
<test logic= "AND" value= "1" >
/controls/gear/tiller-enabled == 0
</test>
</switch>
<fcs_function name= "Nose Wheel Steering 0" >
<function name= "fcs/steer-nose-deg[0]" >
<description > Steering command for nose gear</description>
<sum >
<product >
<table >
<independentVar lookup= "row" > /controls/gear/tiller-cmd-norm</independentVar>
<independentVar lookup= "column" > /controls/flight/rudder</independentVar>
<tableData >
-1 0 1
-1 -70 -70 -70
0 -7 0 7
1 70 70 70
</tableData>
</table>
<property > /controls/gear/tiller-enabled</property>
</product>
<product >
<product >
<property > /controls/flight/rudder</property>
<value > 70</value>
</product>
<property > /controls/gear/tiller-disabled</property>
</product>
</sum>
</function>
</fcs_function>
<!-- simulate rotational friction -->
<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>
</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 0.4800
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= "LIFT" >
<function name= "aero/force/Lift_gain" >
<description > Drag_at_zero_lift</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
2016-11-06 16:03:42 +00:00
<value > 0.30</value>
2016-11-04 22:13:12 +00:00
</product>
</function>
<!-- function name="aero/coefficient/CLalpha">
<description > Lift_due_to_alpha</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<table >
<independentVar lookup= "row" > aero/alpha-rad</independentVar>
<independentVar lookup= "column" > fcs/flap-pos-deg</independentVar>
<tableData >
0.0000 1.0000 9.0000 10.0000 40.0000
-0.0900 -0.2200 -0.2200 -0.1200 -0.1200 0.3200
0.0000 0.2500 0.2500 0.3500 0.3500 0.7500
0.0900 0.7300 0.7300 0.8300 0.8300 1.2300
0.1000 0.8300 0.8300 0.9300 0.9300 1.3300
0.1200 0.9200 0.9200 1.0200 1.0200 1.4200
0.1400 1.0200 1.0200 1.1200 1.1200 1.5200
0.1600 1.0800 1.0800 1.1800 1.1800 1.5800
0.1700 1.1300 1.1300 1.2300 1.2300 1.6300
0.1900 1.1900 1.1900 1.2900 1.2900 1.6900
0.2100 1.2500 1.2500 1.3500 1.3500 1.7700
0.2400 1.3500 1.3700 1.4700 1.4800 1.9300
0.2600 1.4400 1.4700 1.5700 1.6200 2.1200
0.2800 1.4700 1.5100 1.6100 1.7800 2.4000
0.3000 1.5000 1.5600 1.6600 1.9000 2.3000
0.3200 1.4700 1.6100 1.6000 1.7000 2.0300
0.3400 1.3500 1.5000 1.4100 1.5000 1.5300
0.3600 1.1500 1.2000 1.2000 1.2000 1.2000
</tableData>
</table>
</product>
</function-->
<function name= "aero/force/Lift_alpha" >
<description > Lift_due_to_alpha</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 >
0.0000 1.0000 9.0000 10.0000 40.0000
-0.0900 -0.2200 -0.2200 -0.1200 -0.1200 0.2500
0.0000 0.2500 0.2500 0.3500 0.3500 0.7500
0.0900 0.7300 0.7300 0.8300 0.8300 1.2300
0.1000 0.8300 0.8300 0.9300 0.9300 1.3300
0.1200 0.9200 0.9200 1.0200 1.0200 1.4200
0.1400 1.0200 1.0200 1.1200 1.1200 1.5200
0.1600 1.0800 1.0800 1.1800 1.1800 1.5800
0.1700 1.1300 1.1300 1.2300 1.2300 1.6300
0.1900 1.1900 1.1900 1.2900 1.2900 1.6900
0.2100 1.2500 1.2500 1.3500 1.3500 1.7700
0.2400 1.3500 1.3700 1.4700 1.4800 1.9300
0.2600 1.4400 1.4700 1.5700 1.6200 2.1200
0.2800 1.4700 1.5100 1.6100 1.7800 2.4000
0.3000 1.5000 1.5600 1.6600 1.9000 2.3000
0.3200 1.4700 1.6100 1.6000 1.7000 2.0300
0.3400 1.3500 1.5000 1.4100 1.5000 1.5300
0.3600 1.1500 1.2000 1.2000 1.2000 1.2000
</tableData>
</table>
</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 > 0.1930</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 > 0.1930</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 > -0.15</value>
</product>
</function>
</axis>
<axis name= "DRAG" >
<function name= "aero/force/Drag_zero_lift" >
<description > Drag_at_zero_lift</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<value > 0.016</value>
</product>
</function>
<!-- function name="aero/coefficient/CDalpha">
<description > Drag_due_to_alpha</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<table >
<independentVar lookup= "row" > aero/alpha-rad</independentVar>
<independentVar lookup= "column" > fcs/flap-pos-deg</independentVar>
<tableData >
0.0000 1.0000 25.0000 40.0000
-0.0873 0.0041 0.0000 0.0005 0.0014
-0.0698 0.0013 0.0004 0.0025 0.0041
-0.0524 0.0001 0.0023 0.0059 0.0084
-0.0349 0.0003 0.0057 0.0108 0.0141
-0.0175 0.0020 0.0105 0.0172 0.0212
0.0000 0.0052 0.0168 0.0251 0.0399
0.0175 0.0099 0.0248 0.0346 0.0502
0.0349 0.0162 0.0342 0.0457 0.0621
0.0524 0.0240 0.0452 0.0583 0.0755
0.0698 0.0334 0.0577 0.0724 0.0904
0.0873 0.0442 0.0718 0.0881 0.1068
0.1047 0.0566 0.0874 0.1053 0.1248
0.1222 0.0706 0.1045 0.1240 0.1443
0.1396 0.0860 0.1232 0.1442 0.1654
0.1571 0.0962 0.1353 0.1573 0.1790
0.1745 0.1069 0.1479 0.1708 0.1930
0.1920 0.1180 0.1610 0.1849 0.2075
0.2094 0.1298 0.1746 0.1995 0.2226
0.2269 0.1424 0.1892 0.2151 0.2386
0.2443 0.1565 0.2054 0.2323 0.2564
0.2618 0.1727 0.2240 0.2521 0.2767
0.2793 0.1782 0.2302 0.2587 0.2835
0.2967 0.1716 0.2227 0.2507 0.2753
0.3142 0.1618 0.2115 0.2388 0.2631
0.3316 0.1475 0.1951 0.2214 0.2451
0.3491 0.1097 0.1512 0.1744 0.1966
</tableData>
</table>
</product>
</function-->
<function name= "aero/force/Drag_alpha" >
<description > Drag_due_to_alpha</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<table >
<independentVar lookup= "row" > aero/alpha-rad</independentVar>
<independentVar lookup= "column" > fcs/flap-pos-deg</independentVar>
<tableData >
0.0000 1.0000 25.0000 40.0000
-0.0873 0.0041 0.0000 0.0005 0.0014
-0.0698 0.0013 0.0004 0.0025 0.0041
-0.0524 0.0001 0.0023 0.0059 0.0084
-0.0349 0.0003 0.0057 0.0108 0.0141
-0.0175 0.0020 0.0105 0.0172 0.0212
0.0000 0.0052 0.0168 0.0251 0.0399
0.0175 0.0099 0.0248 0.0346 0.0502
0.0349 0.0162 0.0342 0.0457 0.0621
0.0524 0.0240 0.0452 0.0583 0.0755
0.0698 0.0334 0.0577 0.0724 0.0904
0.0873 0.0442 0.0718 0.0881 0.1068
0.1047 0.0566 0.0874 0.1053 0.1248
0.1222 0.0706 0.1045 0.1240 0.1443
0.1396 0.0860 0.1232 0.1442 0.1654
0.1571 0.0962 0.1353 0.1573 0.1790
0.1745 0.1069 0.1479 0.1708 0.1930
0.1920 0.1180 0.1610 0.1849 0.2075
0.2094 0.1298 0.1746 0.1995 0.2226
0.2269 0.1424 0.1892 0.2151 0.2386
0.2443 0.1565 0.2054 0.2323 0.2564
0.2618 0.1727 0.2240 0.2521 0.2767
0.2793 0.1782 0.2302 0.2587 0.2835
0.2967 0.1716 0.2227 0.2507 0.2753
0.3142 0.1618 0.2115 0.2388 0.2631
0.3316 0.1475 0.1951 0.2214 0.2451
0.3491 0.1097 0.1512 0.1744 0.1966
</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 > 0.0500</value>
</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 > 0.055</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>
<property > aero/mag-beta-rad</property>
<value > 0.2000</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>
<property > aero/mag-beta-rad</property>
<value > 0.2000</value>
</product>
</function>
<!-- function name="aero/coefficient/CDgear">
<description > Drag_due_to_landing_gear</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<property > gear/gear-pos-norm</property>
<value > 0.0400</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 > 0.04</value>
</product>
</function>
<!-- function name="aero/coefficient/CDspeedbrake">
<description > Drag_due_to_speedbrake</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<property > fcs/speedbrake-pos-norm</property>
<value > 0.0400</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 > 0.04</value>
</product>
</function>
<!-- function name="aero/coefficient/CDo">
<description > Drag_at_zero_lift</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<value > 0.016</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>
<table >
<independentVar lookup= "row" > velocities/mach</independentVar>
<tableData >
0.00 0.000
0.79 0.000
1.10 0.023
1.80 0.015
</tableData>
</table>
</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>
<table >
<independentVar > aero/beta-rad</independentVar>
<tableData >
-0.3500 0.5000
0.0000 0.0000
0.3500 -0.5000
</tableData>
</table>
</product>
< /function -->
<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/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 > aero/beta-rad</independentVar>
<tableData >
-0.3500 0.0100
0.0000 0.0000
0.3500 -0.0100
</tableData>
</table>
</product>
</function-->
<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 > -0.1</value>
</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>
</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/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 > 0.0050</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 > 0.005</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>
<!- value> 0.2000< /value -> <!- Excesive roll !!! ->
<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_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 -->
0.0 0.080
2.0 0.033
</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 > 0.0050</value>
</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 > 0.005</value>
</product>
</function>
</axis>
<axis name= "PITCH" >
<function name= "aero/moment/Pitch_zero_alpha_and_flaps" >
<description > Pitching_moment_at_zero_alpha</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<property > metrics/cbarw-ft</property>
<table >
<independentVar > fcs/flap-pos-deg</independentVar>
<tableData >
0.0000 0.0000
40.0000 -0.1000
</tableData>
</table>
</product>
</function>
<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> - 4.0000</value> -->
2016-11-05 04:53:20 +00:00
<value > -0.8</value>
2016-11-04 22:13:12 +00:00
</product>
</function>
<function name= "aero/moment/Pitch_elevator" >
<description > Pitch_moment_due_to_elevator_Deflection</description>
<product >
<property > aero/qbar-psf</property>
<property > metrics/Sw-sqft</property>
<property > metrics/cbarw-ft</property>
<property > fcs/elevator-pos-rad</property>
<!-- <value> - 1.5000</value> Excesive Pitch -->
<table >
<independentVar lookup= "row" > velocities/mach</independentVar>
<tableData >
<!-- 0.0 - 1.200 -->
0.0 -1.000
2.0 -0.300
</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> - 10.0000</value -->
<value > -10</value>
</product>
</function>
<function name= "aero/moment/Pitch_alpha_rate" >
<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> - 12.0000</value -->
<value > -12</value>
</product>
</function>
</axis>
<axis name= "YAW" >
<!-- 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 > -0.0400</value>
</product>
</function-->
<function name= "aero/moment/Yaw_damp" >
<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 > -0.15</value>
</product>
</function>
<!-- 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 > 0.2000</value>
</product>
</function-->
<function name= "aero/moment/Yaw_beta" >
<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 > 0.12</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> -0.5000</value> Excesive Yaw->
<value > -0.3</value>
</product>
</function-->
<function name= "aero/moment/Yaw_rudder" >
<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> - 0.2</value -->
<value > -0.15</value>
</product>
</function>
<!-- function name="aero/moment/Yaw_aileron">
<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</value>
</product>
</function-->
</axis>
</aerodynamics>
<external_reactions >
<force name= "pushback" frame= "BODY" >
<location unit= "IN" >
<x > 294</x>
<y > 0</y>
<z > -149</z>
</location>
<direction >
<x > 1</x>
<y > 0</y>
<z > 0</z>
</direction>
</force>
</external_reactions>
</fdm_config>
