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fokker50.xml
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fokker50.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<!--
Reference:
http://www.dtic.mil/dtic/tr/fulltext/u2/a257974.pdf
-->
<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> Erik Hofman </author>
<filecreationdate> 2002-01-01</filecreationdate>
<version> $Revision: 1.22 $ </version>
<description> Fokker 50 commercial turboprop airliner </description>
<reference refID="None" author="n/a" title="n/a" date="n/a"/>
</fileheader>
<metrics>
<wingarea unit="FT2"> 753.55 </wingarea>
<wingspan unit="FT"> 95.15 </wingspan>
<wing_incidence> 3.27 </wing_incidence>
<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="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">
<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="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">
<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">
<property value="0" type="float">/systems/fokker50/erp/settingn</property>
<property value="0" type="float">/systems/fokker50/erp/settinggi</property>
<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="Thruster">
<summer name="Thrust Coefficient Left">
<input>propulsion/engine[0]/thrust-coefficient</input>
<output>systems/propulsion/thrust-coefficient-left</output>
</summer>
<summer name="Thrust Coefficient Right">
<input>propulsion/engine[1]/thrust-coefficient</input>
<output>systems/propulsion/thrust-coefficient-right</output>
</summer>
<summer name="Thrust Coefficient Left-Right">
<input>systems/propulsion/thrust-coefficient-left</input>
<input>-systems/propulsion/thrust-coefficient-right</input>
<output>systems/propulsion/thrust-coefficient-left-right</output>
</summer>
<summer name="Thrust Coefficient">
<input>systems/propulsion/thrust-coefficient-left</input>
<input>systems/propulsion/thrust-coefficient-right</input>
<output>systems/propulsion/thrust-coefficient</output>
</summer>
</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>
<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>
</function>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<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>
</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 1.4083
-0.3400 0.0806
0.0000 0.0245
0.3400 0.0806
1.5700 1.4083
</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>0.0300</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>0.0011</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>0.0460</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>0.0400</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>-0.4157</value>
</product>
</function>
<function name="aero/force/Side_roll_rate">
<description>Side_force_due_to_roll_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table>
<independentVar lookup="row">aero/Re</independentVar>
<tableData>
9657151 0.4339
10622865 0.0324
14485727 0.0144
19153512 0.0082
</tableData>
</table>
</product>
</function>
<function name="aero/force/Side_yaw_rate">
<description>Side_force_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value> 0.3618 </value>
</product>
</function>
<function name="aero/force/Side_rudder">
<description>Side_force_due_to_rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value> 0.2532 </value>
</product>
</function>
</axis>
<axis name="LIFT">
<function name="aero/force/Lift_propwash">
<description>Delta lift due to propeller induced velocity</description>
<product>
<property>systems/propulsion/thrust-coefficient</property>
<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>
0.0 60.0
-0.15 0.000 0.000
0.00 0.057 0.151
0.38 0.299 0.797
0.75 0.000 0.000
</tableData>
</table>
</product>
</function>
<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 -0.6932
0.0000 0.4678
0.3400 2.4669
0.6000 0.8813
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_pitch_rate">
<description>Lift_due_to_pitch_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>velocities/q-aero-rad_sec</property>
<property>aero/ci2vel</property>
<value> 5.2170 </value>
</product>
</function>
<function name="aero/force/Lift_alpha_rate">
<description>Lift_due_to_alpha_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/alphadot-rad_sec</property>
<property>aero/ci2vel</property>
<value> 1.4906 </value>
</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/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>0.2732</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/moment/Roll_differential_propwash">
<description>Roll moment due to differential propwash</description>
<product>
<property>systems/propulsion/thrust-coefficient-left-right</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/alpha-rad</property>
<value> -1.7213 </value>
</product>
</function>
<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>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
9657151 10622865 14485727 19153512
-0.0349 -0.2127 -0.0369 -0.0290 -0.0265
0.3491 -0.3313 -0.0478 -0.0406 -0.0391
</tableData>
</table>
</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>-0.5138</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>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
9657151 10622865 14485727 19153512
-0.0349 0.7227 0.1035 0.0758 0.0663
0.3491 6.8236 0.6608 0.6331 0.6236
</tableData>
</table>
</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 0.0375
</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/moment/Pitch_propwash">
<description>Pitch moment due to propeller induced velocity</description>
<product>
<property>systems/propulsion/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 60.0
-0.01 0.000 0.000
0.00 -0.035 -0.093
0.38 -0.185 -0.492
0.49 0.000 0.000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<value>-1.8763</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 -1.6280
2.0000 -0.4070
</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>-20.1341</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>-5.7526</value>
</product>
</function>
</axis>
<axis name="YAW">
<!-- Stall initiator -->
<function name="aero/moment/Yaw_alpha">
<description>Yaw moment due to alpha</description>
<product>
<property>aero/qbar-psf</property>