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F-104S.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="F-104C" version="2.0" release="ALPHA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
<author> Aeromatic v 0.91 </author>
<filecreationdate>2009-08-14</filecreationdate>
<version>$Revision: 1.25 $</version>
<description>Models an F-104C</description>
<note>
This model was created using publicly available data, publicly available
technical reports, textbooks, and guesses. It contains no proprietary or
restricted data. If this model has been validated at all, it would be
only to the extent that it seems to "fly right", and that it possibly
complies with published, publicly known, performance data (maximum speed,
endurance, etc.). Thus, this model is meant for educational and entertainment
purposes only.
This simulation model is not endorsed by the manufacturer. This model is not
to be sold.
</note>
</fileheader>
<!--
File: F-104C-jsbsim.xml
Inputs:
name: F-104C
type: single-engine transonic/supersonic fighter
max weight: 27855 lb
wing span: 21.94 ft
length: 54.77 ft
wing area: 196.1 sq-ft
gear type: tricycle
retractable?: yes
# engines: 1
engine type: turbine
engine layout: aft fuselage
yaw damper? yes
Outputs:
wing loading: 105 lb/sq-ft
CL-alpha: 3.5 per radian
CL-0: 0.08
CL-max: 1
CD-0: 0.021
K: 0.12
-->
<!--
Note:
All tables that contain data due to Mach 0.257 and 1.8 are taken from Roskam
-->
<metrics>
<wingarea unit="FT2">196.10</wingarea>
<wingspan unit="FT" >21.94</wingspan>
<wing_incidence>0</wing_incidence>
<chord unit="FT" >9.55</chord>
<htailarea unit="FT2">48.20</htailarea>
<htailarm unit="FT" > 46.86</htailarm>
<vtailarea unit="FT2">43.70</vtailarea>
<vtailarm unit="FT" >23.23</vtailarm>
<location name="AERORP" unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
<location name="EYEPOINT" unit="IN">
<x>143</x>
<y>0.0</y>
<z>-4.25</z>
</location>
<location name="VRP" unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2">3663</ixx>
<iyy unit="SLUG*FT2">59000</iyy> <!-- orig: 38362, Rk: 59000 -->
<izz unit="SLUG*FT2">60000</izz> <!-- orig: 24572, Rk: 60000 -->
<ixy unit="SLUG*FT2">0</ixy>
<ixz unit="SLUG*FT2">0</ixz>
<iyz unit="SLUG*FT2">0</iyz>
<emptywt unit="LBS" >12760</emptywt>
<location name="CG" unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
<pointmass name="left-tip-tank"><!--empty-->
<weight unit="LBS">125</weight>
<location name="POINTMASS" unit="IN">
<x>389</x>
<y>-148</y>
<z>-52</z>
</location>
</pointmass>
<pointmass name="right-tip-tank"><!--empty-->
<weight unit="LBS">125</weight>
<location name="POINTMASS" unit="IN">
<x>389</x>
<y>148</y>
<z>-52</z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x>213</x>
<y>0.0</y>
<z>-132</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 6723.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2241.00 </damping_coeff>
<max_steer unit="DEG">60.00</max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x>393.6</x>
<y>-63.20</y>
<z>-121</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>LEFT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MAIN">
<location unit="IN">
<x>393.6</x>
<y>63.20</y>
<z>-121</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group>RIGHT</brake_group>
<retractable>1</retractable>
</contact>
<contact type="STRUCTURE" name="NOSE">
<location unit="IN">
<x>0</x>
<y>0</y>
<z>-43</z>
</location>
<static_friction>0.80</static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL">
<location unit="IN">
<x>656</x>
<y>0</y>
<z>-2.5</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x>422.4</x>
<y>-166.5</y>
<z>-54.6</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x>422.4</x>
<y>166.5</y>
<z>-54.6</z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 22410.00 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4482.00 </damping_coeff>
</contact>
</ground_reactions>
<propulsion>
<engine file="J79-GE-11A">
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<thruster file="direct">
<location unit="IN">
<x>622.05</x>
<y>0.00</y>
<z>-23.29</z>
</location>
<orient unit="DEG">
<pitch>0.0</pitch>
<roll>0.0</roll>
<yaw>0.0</yaw>
</orient>
</thruster>
</engine>
<!--internal-->
<tank type="FUEL" number="0">
<location unit="IN">
<x>319.5</x>
<y>0.0</y>
<z>-35.08</z>
</location>
<capacity unit="LBS">6050.00</capacity>
<contents unit="LBS">5000.00</contents>
</tank>
<!--left tip tank-->
<tank type="FUEL" number="1">
<location unit="IN">
<x>389</x>
<y>-148</y>
<z>-52</z>
</location>
<capacity unit="LBS">1400.00</capacity>
<contents unit="LBS">1000.00</contents>
</tank>
<!--right tip tank-->
<tank type="FUEL" number="2">
<location unit="IN">
<x>389</x>
<y>148</y>
<z>-52</z>
</location>
<capacity unit="LBS">1400.00</capacity>
<contents unit="LBS">1000.00</contents>
</tank>
</propulsion>
<system file="armament"/>
<system file="beacon"/>
<system file="BLC"/>
<system file="canopy"/>
<system file="chute"/>
<!--<system file="crash-detect"/>-->
<system file="FCS-pitch"/>
<system file="FCS-roll"/>
<system file="FCS-yaw"/>
<system file="flaps"/>
<system file="gear"/>
<system file="NWS"/>
<!--<system file="radar"/>-->
<system file="speedbrakes"/>
<system file="tailhook"/>
<flight_control name="FCS"></flight_control>
<aerodynamics>
<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 1.2290
0.1000 1.1240
0.1500 1.1160
0.2000 1.1240
0.3000 1.1050
0.4000 1.0410
0.5000 1.0340
0.6000 1.0190
0.7000 1.0080
0.8000 1.0030
0.9000 1.0010
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</function>
<axis name="LIFT">
<function name="aero/coefficient/CLo">
<description>Lift_at_zero_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.4000 0.0100
0.6000 0.0100
0.8000 0.0100
0.9000 0.0100
1.0000 -0.0100
1.2000 -0.0200
1.4000 0.0400
1.6000 0.0320
1.8000 0.0200
2.0000 0.0100
</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/alpha-rad</property>
<property>velocities/mach</property>
<property>aero/function/kCLge</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.4000 7.1154
0.6000 4.8432
0.8000 4.2637
0.9000 4.3529
1.0000 4.2055
1.2000 3.1401
1.4000 2.2916
1.6000 1.7603
1.8000 1.3831
2.0000 1.1042
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLDf">
<description>Delta_lift_due_to_flap_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/function/kCLge</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 7.0000 13.0000
0.6500 0.0000 0.0890 0.4000
0.7000 0.0000 0.0890 0.3810
0.7500 0.0000 0.0990 0.3410
0.8000 0.0000 0.1080 0.3520
0.8500 0.0000 0.1280 0.3460
0.9000 0.0000 0.1380 0.1390
0.9500 0.0000 0.1280 0.2900
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLDh">
<description>Lift_due_to_Horizontal_tail_Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/elevator-pos-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.6800
1.8000 0.5200
</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>velocities/mach</independentVar>
<tableData>
0.2570 2.3000
1.8000 1.9000
</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>velocities/mach</independentVar>
<tableData>
0.2570 0.6600
1.8000 0.8200
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/dCLslat">
<description>Delta_Lift_due_to_slats</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
<tableData>
0.00 0.025
0.30 0.125
1.00 0.25
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CLBLC">
<description>Delta_Lift_due_to_BLC</description>
<product>
<property>systems/BLC/active</property>
<value> 0.2 </value>
</product>
</function>
<function name="aero/coefficient/dCLsb">
<description>Delta_Lift_due_to_speedbrake</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0</value>
</product>
</function>
</axis>
<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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0160
0.8000 0.0160
0.8500 0.0163
0.8800 0.0170
0.9000 0.0170
0.9250 0.0190
0.9500 0.0230
0.9750 0.0310
1.0000 0.0380
1.0500 0.0470
1.1000 0.0500
1.1500 0.0500
1.2000 0.0490
1.4000 0.0468
1.6000 0.0440
1.8000 0.0430
2.0000 0.0422
</tableData>
</table>
</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">velocities/mach</independentVar>
<tableData>
0.0000 0.8000 0.9000 1.0000 1.2000 1.4000 1.6000 1.8000 2.0000
-0.0700 0.0034 0.0049 0.0059 0.0093 0.0109 0.0040 0.0035 0.0042 0.0041
-0.0350 0.0010 0.0013 0.0015 0.0026 0.0032 0.0010 0.0011 0.0017 0.0018
0.0000 0.0002 0.0002 0.0001 0.0002 0.0006 0.0011 0.0010 0.0008 0.0004
0.0350 0.0024 0.0022 0.0031 0.0036 0.0046 0.0072 0.0059 0.0052 0.0037
0.0700 0.0093 0.0118 0.0165 0.0195 0.0187 0.0243 0.0198 0.0161 0.0133
0.1050 0.0240 0.0332 0.0465 0.0472 0.0425 0.0506 0.0430 0.0345 0.0176
0.1400 0.0465 0.0589 0.0822 0.0860 0.0788 0.0837 0.0722 0.0593 0.0479
0.1750 0.0703 0.0851 0.1361 0.1674 0.1298 0.1257 0.1052 0.0894 0.0741
0.2090 0.1074 0.1205 0.1988 0.3273 0.2195 0.1945 0.1487 0.1220 0.1013
0.2440 0.1679 0.1684 0.2999 0.6122 0.3791 0.3195 0.1529 0.1650 0.1331
</tableData>
</table>
</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 lookup="row">aero/beta-rad</independentVar>
<tableData>
-1.57 1.230
-0.26 0.050
0.00 0.000
0.26 0.050
1.57 1.230
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDdh">
<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>0.04</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>
<table>
<independentVar>gear/gear-pos-norm</independentVar>
<tableData>
0.0000 0.0000
0.3000 0.1000
1.0000 0.0600
</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>
<value>0.002679</value>
</product>
</function>
<function name="aero/coefficient/CDslat">
<description>Drag_due_to_slats</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">fcs/flap-pos-norm</independentVar>
<tableData>
0.00 0.003
0.30 0.015
1.00 0.03
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CDbc">
<description>Drag_due_to_braking_chute</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>systems/chute/unfurl-norm</property>
<value>.75</value>
</product>
</function>
<function name="aero/coefficient/CDsb">
<description>Drag_due_to_speedbrakes</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/speedbrake-pos-norm</property>
<value>0.04</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -1.1800
1.8000 -1.0450
</tableData>
</table>
</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.3290
1.8000 0.0870
</tableData>
</table>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.1750
1.8000 -0.0930
</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-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.2850
1.8000 -0.2720
</tableData>
</table>
</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-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.2650
1.8000 0.1540
</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>
0.2570 0.0392
1.8000 0.0173
</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.0448
1.8000 0.0079
</tableData>
</table>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cmalpha">
<description>Pitch_moment_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>aero/alpha-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.6440
1.8000 -1.3080
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cmo">
<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>velocities/mach</independentVar>
<tableData>
0.2570 0.0300
1.8000 -0.0280
</tableData>
</table>
</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 lookup="row">velocities/mach</independentVar>
<tableData>
0.0 -0.800
2.0 -0.200
</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-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -5.84
1.8000 -4.83
</tableData>
</table>
</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -1.6400
1.8000 -2.0500
</tableData>
</table>
</product>
</function>
</axis>
<axis name="YAW">
<function name="aero/coefficient/Cnb">
<description>Yaw_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/beta-rad</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.5070
1.8000 0.2420
</tableData>
</table>
</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-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.1440
1.8000 -0.0930
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnr">
<description>Yaw_moment_due_to_yaw_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-rad_sec</property>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.7530
1.8000 -0.6490
</tableData>
</table>
</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -0.1645
1.8000 -0.0435
</tableData>
</table>
</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 0.0042
1.8000 0.0025
</tableData>
</table>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>