jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<fdm_config name="Cessna 310 Light Twin General Aviation Aircraft" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> David Megginson </author>
<author> Tony Peden </author>
<author> Jon Berndt </author>
<filecreationdate> 2001-11-24 </filecreationdate>
<version> $Revision: 1.64 $ </version>
<description>
Models a C310 light twin. The airplane has a wingspan of 35.98 feet, wing area of 178 square feet,
an aspect ratio of 7.3, and an M.A.C. of 5 feet based on projection of the outboard leading edge
of the wing through the fuselage. The wing airfoil section is a modified NACA 64(2)A215 airfoil
with the trailing edge cusp faired out. The wing has 5 degrees of dihedral, no twist, and is at 2 degrees
positive incidence with respect to the fuselage reference line. Thrust axes are parallel to the reference line.
The horizontal tail is all-movable, with a deflection range of 4 to -14 degrees. Control deflection
range for the ailerons is 14 to -18 degrees. Normal rudder deflection range is +/-27 degrees.
</description>
<license
licenseName="GPL (General Public License)"
licenseURL="http://www.gnu.org/licenses/gpl.html"/>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. If this model has been validated at all, it would be
only to the extent that it seems to "fly right", and that it possibly
complies with published, publicly known, performance data (maximum speed,
endurance, etc.). Thus, this model is meant for educational and entertainment
purposes only.
This simulation model is not endorsed by the manufacturer. This model is not
to be sold.
</note>
<reference title="Full-Scale Wind Tunnel Investigation of Static Longitudinal and Lateral Characteristics of a Light Twin-Engine Airplane"
author="Marvin P. Fink, Delma C. Freeman, Jr."
date="1969-01-01" refID="NASA TN D-4983"/>
</fileheader>
<metrics>
<wingarea unit="FT2"> 175 </wingarea>
<wingspan unit="FT"> 36.5 </wingspan>
<chord unit="FT"> 4.9 </chord>
<htailarea unit="FT2"> 21.9 </htailarea>
<htailarm unit="FT"> 15.7 </htailarm>
<vtailarea unit="FT2"> 16.5 </vtailarea>
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x> 46 </x>
<y> 0 </y>
<z> 8.6 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 35 </x>
<y> -12 </y>
<z> 38 </z>
</location>
<location name="VRP" unit="IN">
<x> 46 </x>
<y> 0 </y>
<z> 8.6 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 8884 </ixx>
<iyy unit="SLUG*FT2"> 1939 </iyy>
<izz unit="SLUG*FT2"> 11001 </izz>
<emptywt unit="LBS"> 2950 </emptywt>
<location name="CG" unit="IN">
<x> 46 </x>
<y> 0 </y>
<z> 8.6 </z>
</location>
<pointmass name="Pilot">
<weight unit="LBS"> 180 </weight>
<location unit="IN">
<x> 37 </x>
<y> -14 </y>
<z> 24 </z>
</location>
</pointmass>
<pointmass name="Co-Pilot">
<weight unit="LBS"> 180 </weight>
<location unit="IN">
<x> 37 </x>
<y> 14 </y>
<z> 24 </z>
</location>
</pointmass>
<pointmass name="Pilot's wife">
<weight unit="LBS"> 150 </weight>
<location unit="IN">
<x> 61 </x>
<y> -14 </y>
<z> 24 </z>
</location>
</pointmass>
<pointmass name="Co-Pilot's husband">
<weight unit="LBS"> 150 </weight>
<location unit="IN">
<x> 61 </x>
<y> 14 </y>
<z> 24 </z>
</location>
</pointmass>
<pointmass name="Luggage">
<weight unit="LBS"> 100 </weight>
<location unit="IN">
<x> 90 </x>
<y> 0 </y>
<z> 24 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> -60.2 </x>
<y> 0 </y>
<z> -27 </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"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
<max_steer unit="DEG"> 10 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x> 50.7 </x>
<y> -70.8 </y>
<z> -31 </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"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x> 50.7 </x>
<y> 70.8 </y>
<z> -31 </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"> 5400 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1600 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="TAIL_SKID">
<location unit="IN">
<x> 221.8 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 20000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x> -96.3 </x>
<y> 0 </y>
<z> 10.3 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="CABIN_LEFT">
<location unit="IN">
<x> 0 </x>
<y> -25 </y>
<z> 0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="CABIN_RIGHT">
<location unit="IN">
<x> 0 </x>
<y> 25 </y>
<z> 0 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="ROOF">
<location unit="IN">
<x> 41.3 </x>
<y> 0 </y>
<z> 53.3 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_TIP">
<location unit="IN">
<x> 48.1 </x>
<y> -222 </y>
<z> 18.9 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_TIP">
<location unit="IN">
<x> 48.1 </x>
<y> 222 </y>
<z> 18.9 </z>
</location>
<static_friction> 0.2 </static_friction>
<dynamic_friction> 0.2 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 10000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2000 </damping_coeff>
</contact>
</ground_reactions>
<propulsion>
<engine file="engIO470D">
<location unit="IN">
<x> -27.5 </x>
<y> -70 </y>
<z> 15.5 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<thruster file="propC10v">
<location unit="IN">
<x> -27.5 </x>
<y> -70 </y>
<z> 15.5 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
<sense> 1 </sense>
<p_factor> 0.1 </p_factor>
</thruster>
</engine>
<engine file="engIO470D">
<location unit="IN">
<x> -27.5 </x>
<y> 70 </y>
<z> 15.5 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<thruster file="propC10v">
<location unit="IN">
<x> -27.5 </x>
<y> 70 </y>
<z> 15.5 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
<sense> 1 </sense>
<p_factor> 0.1 </p_factor>
</thruster>
</engine>
<tank type="FUEL"> <!-- Tank number 0 -->
<location unit="IN">
<x> 35 </x>
<y> -209.8 </y>
<z> 28.3 </z>
</location>
<capacity unit="LBS"> 336 </capacity>
<contents unit="LBS"> 225 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 1 -->
<location unit="IN">
<x> 35 </x>
<y> 209.8 </y>
<z> 28.3 </z>
</location>
<capacity unit="LBS"> 336 </capacity>
<contents unit="LBS"> 225 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 2 -->
<location unit="IN">
<x> 35 </x>
<y> -41.6 </y>
<z> 11.7 </z>
</location>
<capacity unit="LBS"> 135 </capacity>
<contents unit="LBS"> 95 </contents>
</tank>
<tank type="FUEL"> <!-- Tank number 3 -->
<location unit="IN">
<x> 35 </x>
<y> 41.6 </y>
<z> 11.7 </z>
</location>
<capacity unit="LBS"> 135 </capacity>
<contents unit="LBS"> 95 </contents>
</tank>
</propulsion>
<system file="GNCUtilities"/>
<autopilot file="c310ap">
<!-- Roll channel A/P gains -->
<property value="50.0"> ap/roll-pid-kp </property>
<property value="5.0"> ap/roll-pid-ki </property>
<property value="17.0"> ap/roll-pid-kd </property>
</autopilot>
<flight_control name="Cessna 310">
<channel name="Pitch">
<summer name="Pitch Trim Sum">
<input>ap/elevator_cmd</input>
<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> -14.0 </min>
<max> 4.0 </max>
</range>
<gain>0.01745</gain>
<output>fcs/elevator-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Elevator position normalized">
<input>fcs/elevator-pos-deg</input>
<domain>
<min>-25</min>
<max>35</max>
</domain>
<range>
<min>-1</min>
<max>1</max>
</range>
<output>fcs/elevator-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Roll">
<summer name="Roll Trim Sum">
<input>ap/aileron_cmd</input>
<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> <!-- input is normalized -->
<range>
<min> -18.0 </min> <!-- map to degree limits -->
<max> 14.0 </max>
</range>
<gain>0.01745</gain> <!-- convert to radians -->
<output>fcs/left-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Left Aileron Control Normalized">
<input>fcs/left-aileron-control</input>
<domain>
<min> -0.3141 </min> <!-- -18 degrees -->
<max> 0.2443 </max> <!-- +14 degrees -->
</domain>
<range>
<min> -1.0 </min>
<max> 1.0 </max>
</range>
<output>fcs/left-aileron-pos-norm</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control">
<input>-fcs/roll-trim-sum</input>
<range>
<min> -18.0 </min>
<max> 14.0 </max>
</range>
<gain>0.01745</gain>
<output>fcs/right-aileron-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Right Aileron Control Normalized">
<input>fcs/right-aileron-control</input>
<domain>
<min> -0.3141 </min> <!-- -18 degrees -->
<max> 0.2443 </max> <!-- +14 degrees -->
</domain>
<range>
<min> -1.0 </min>
<max> 1.0 </max>
</range>
<output>fcs/right-aileron-pos-norm</output>
</aerosurface_scale>
</channel>
<channel name="Yaw">
<summer name="Yaw Trim Sum">
<input>ap/rudder_cmd</input>
<input>fcs/rudder-cmd-norm</input>
<input>fcs/yaw-trim-cmd-norm</input>
<clipto>
<min>-1</min>
<max>1</max>
</clipto>
</summer>
<aerosurface_scale name="Rudder Control">
<input>fcs/yaw-trim-sum</input>
<gain>0.01745</gain>
<range>
<min>-27.</min>
<max> 27</max>
</range>
<output>fcs/rudder-pos-rad</output>
</aerosurface_scale>
<aerosurface_scale name="Rudder position normalized">
<input>fcs/rudder-pos-deg</input>
<domain>
<min>-27</min>
<max> 27</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>15</position>
<time>2</time>
</setting>
<setting>
<position>25</position>
<time>1</time>
</setting>
<setting>
<position>45</position>
<time>1</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>45</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>5</time>
</setting>
</traverse>
<output>gear/gear-pos-norm</output>
</kinematic>
</channel>
<channel name="Automatic Mixture Control">
<fcs_function name="systems/mixture-cmd-norm">
<function>
<quotient>
<table>
<independentVar lookup="row">atmosphere/P-psf</independentVar>
<tableData>
50 0.1
990 0.5
1300 0.675
2117 1.0
</tableData>
</table>
<value>1.0</value>
</quotient>
</function>
</fcs_function>
<pure_gain name="systems/mixture-pos-norm[0]">
<input> fcs/mixture-cmd-norm[0]</input>
<gain> systems/mixture-cmd-norm</gain>
<output>fcs/mixture-pos-norm[0]</output>
</pure_gain>
<pure_gain name="systems/mixture-pos-norm[1]">
<input> fcs/mixture-cmd-norm[1]</input>
<gain> systems/mixture-cmd-norm</gain>
<output>fcs/mixture-pos-norm[1]</output>
</pure_gain>
</channel>
</flight_control>
<aerodynamics>
<function name="aero/function/kCLge">
<description>Change_in_lift_due_to_ground_effect</description>
<product>
<table>
<independentVar>aero/h_b-mac-ft</independentVar>
<tableData>
0.0000 1.2030
0.1000 1.1270
0.1500 1.0900
0.2000 1.0730
0.3000 1.0460
0.4000 1.0550
0.5000 1.0190
0.6000 1.0130
0.7000 1.0080
0.8000 1.0060
0.9000 1.0030
1.0000 1.0020
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<axis name="DRAG">
<function name="aero/coefficient/CDo">
<description>Drag_at_zero_lift</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value>0.028</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>aero/alpha-rad</independentVar>
<tableData>
-3.14 0.01
-1.51 1.
-0.785 0.707
-0.0873 0.0041
-0.0698 0.0013
-0.0524 0.0001
-0.0349 0.0003
-0.0175 0.0020
0.0000 0.0052
0.0175 0.0099
0.0349 0.0162
0.0524 0.0240
0.0698 0.0334
0.0873 0.0442
0.1047 0.0566
0.1222 0.0706
0.1396 0.0860
0.1571 0.0962
0.1745 0.1069
0.1920 0.1180
0.2094 0.1298
0.2269 0.1424
0.2443 0.1565
0.2618 0.1727
0.2793 0.1782
0.2967 0.1716
0.3142 0.1618
0.3316 0.1475
0.3491 0.1097
0.785 0.707
1.57 1.00
3.14 0.01
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDDf">
<description>Delta_drag_due_to_flap_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.000
15.0000 0.020
25.0000 0.040
45.0000 0.060
</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>0.0000</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>0.1400</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>0.0600</value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/coefficient/CYbeta">
<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>
-0.3490 0.2120
0.0000 0.0000
0.3490 -0.2120
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CYp">
<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/r-aero-rad_sec</property>
<value>-0.1410</value>
</product>
</function>
<function name="aero/coefficient/CYr">
<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>0.3550</value>
</product>
</function>
<function name="aero/coefficient/CYDr">
<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>0.2300</value>
</product>
</function>
</axis>
<axis name="LIFT">
<function name="aero/coefficient/CLo">
<description>Lift_at_zero_alpha. This data is extrapolated from the reference
featured in the file header notes.</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0 0.280
15.0 0.526
25.0 0.723
45.0 1.018
60.0 1.264
</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>
-3.1416 0.0
-2.356 0.97
-1.57 0.0
-0.785 -0.970
-0.3000 -1.0100
-0.2820 -1.1720
-0.2470 -1.0870
-0.2120 -0.9480
-0.1780 -0.8100
0.0000 0.0000
0.1040 0.4760
0.1390 0.6160
0.1740 0.7540
0.2090 0.8570
0.2440 0.9470
0.2790 0.8990
0.3000 0.8060
0.3140 0.5690
0.3490 0.2880
0.6 0.904
0.785 0.97
1.57 0.0
2.356 -0.97
3.14159 0
</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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-1.57 0.0
0.0000 -0.8100
0.0873 -0.9000
0.1152 -0.7700
1.57 0.0
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLadot">
<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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 5.3000
0.0873 4.5000
0.1152 4.1000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLq">
<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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 9.7000
0.0873 8.8000
0.1152 8.4000
</tableData>
</table>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clbeta">
<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>
-0.3490 0.0382
0.0000 0.0000
0.3490 -0.0382
</tableData>
</table>
</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>-0.7500</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>0.0729</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>0.1720</value>
</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>0.0192</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cmo">
<description>Pitch_moment_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<value>0.070</value>
</product>
</function>
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<value>-0.989</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>-12.7000</value>
</product>
</function>
<function name="aero/coefficient/Cmq">
<description>Pitch_moment_due_to_pitch_rate_(pitch_damping)</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>-80.0000</value>
</product>
</function>
<function name="aero/coefficient/CmDe">
<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>-2.2600</value>
</product>
</function>
<function name="aero/coefficient/CmDf">
<description>Pitch_moment_due_to_flap_deflection</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>
0.0 0.000
15.0 -0.05
25.0 -0.10
45.0 -0.15
</tableData>
</table>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnbeta">
<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>0.1000</value>
</product>
</function>
<function name="aero/coefficient/Cnp">
<description>Yaw_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>-0.0257</value>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate_(yaw_damping)</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>-0.3000</value>
</product>
</function>
<function name="aero/coefficient/CnDa">
<description>Yaw_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>-0.0168</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>-0.1152</value>
</product>
</function>
</axis>
</aerodynamics>
<!--
<output name="C310.csv" type="CSV" rate="5">
<simulation> OFF </simulation>
<atmosphere> OFF </atmosphere>
<massprops> OFF</massprops>
<aerosurfaces> OFF </aerosurfaces>
<rates> ON </rates>
<velocities> ON </velocities>
<forces> ON </forces>
<moments> ON </moments>
<position> ON </position>
<propulsion> ON </propulsion>
<fcs> OFF </fcs>
<ground_reactions> OFF </ground_reactions>
<coefficients> OFF </coefficients>
<property> position/long-gc-rad </property>
<property> position/lat-gc-rad </property>
<property> position/h-agl-ft </property>
</output>
-->
<!--
<output name="localhost" type="SOCKET" port="1138" rate="2">
<simulation> OFF </simulation>
<atmosphere> OFF </atmosphere>
<massprops> OFF</massprops>
<aerosurfaces> OFF </aerosurfaces>
<rates> OFF </rates>
<velocities> OFF </velocities>
<forces> OFF </forces>
<moments> OFF </moments>
<position> OFF </position>
<propulsion> OFF </propulsion>
<fcs> OFF </fcs>
<ground_reactions> OFF </ground_reactions>
<coefficients> OFF </coefficients>
<property> position/h-agl-ft </property>
<property> velocities/vc-kts </property>
</output>
<output name="localhost" type="SOCKET" port="1139" rate="2">
<property> propulsion/engine[0]/advance-ratio </property>
<property> propulsion/engine[0]/advance-ratio </property>
<property> forces/fbx-gear-lbs </property>
</output>
-->
</fdm_config>