jsbsim.js
Version:
JSBSim flight dynamics model ported to JavaScript
995 lines (974 loc) • 41.5 kB
text/xml
<fdm_config name="F22" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<fileheader>
Erik Hofman<author> </author>
<filecreationdate> 2004-01-01 </filecreationdate>
<version> $Revision: 1.1 $ </version>
<description> Models an F-22 Raptor </description>
<license>
<licenseName>GPL (General Public License)</licenseName>
<licenseURL>http://www.gnu.org/licenses/gpl.html</licenseURL>
</license>
<note>
This model was created using data that is, or has been, publically
available by means of technical reports, textbooks, image graphs or
published code. This aircraft description file is in no way related
to the manufacturer of the real aircraft.
Neither the name of (any of) the authors nor the names of (any of) the
manufacturers may be used to endorse or promote products derived from
this file.
The data is provided ''as is'' and any express or implied
warranties, including, but not limitted to the implied warranties of
merchantability and fitness for a particular purpose are disclaimed.
</note>
</fileheader>
<metrics>
<wingarea unit="FT2"> 840.0 </wingarea>
<wingspan unit="FT"> 44.49 </wingspan>
<chord unit="FT"> 23.06 </chord>
<htailarea unit="FT2"> 238.9 </htailarea>
<htailarm unit="FT"> 18.66 </htailarm>
<vtailarea unit="FT2"> 158.2 </vtailarea>
<vtailarm unit="FT"> 0 </vtailarm>
<location name="AERORP" unit="IN">
<x> 446.5 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 148.8 </x>
<y> 0 </y>
<z> 38 </z>
</location>
<location name="VRP" unit="IN">
<x> 100 </x>
<y> 0 </y>
<z> 0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 40843 </ixx>
<iyy unit="SLUG*FT2"> 204751 </iyy>
<izz unit="SLUG*FT2"> 258201 </izz>
<ixz unit="SLUG*FT2"> 520 </ixz>
<emptywt unit="LBS"> 43430 </emptywt>
<location name="CG" unit="IN">
<x> 446.5 </x>
<y> 0 </y>
<z> -18.6 </z>
</location>
<pointmass name="Pilot">
<weight unit="LBS"> 230 </weight>
<location name="POINTMASS" unit="IN">
<x> 148.8 </x>
<y> 0 </y>
<z> 20 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> 96.7 </x>
<y> 0 </y>
<z> -89.3 </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"> 18603.4 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 6201.1 </damping_coeff>
<max_steer unit="DEG"> 5 </max_steer>
<brake_group> NONE </brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MLG">
<location unit="IN">
<x> 468.8 </x>
<y> -48 </y>
<z> -89.3 </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"> 62011.2 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 12402.2 </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> 468.8 </x>
<y> 48 </y>
<z> -89.3 </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"> 62011.2 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 12402.2 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable>1</retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="F119-PW-1">
<location unit="IN">
<x> 684.131 </x>
<y> -20 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>0</feed>
<thruster file="direct">
<location unit="IN">
<x> 684.131 </x>
<y> -20 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="F119-PW-1">
<location unit="IN">
<x> 684.131 </x>
<y> 20 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0 </pitch>
<yaw> 0 </yaw>
</orient>
<feed>1</feed>
<thruster file="direct">
<location unit="IN">
<x> 684.131 </x>
<y> 20 </y>
<z> 0 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL">
<location unit="IN">
<x> 446.478 </x>
<y> 0 </y>
<z> -18.6033 </z>
</location>
<capacity unit="LBS"> 7000 </capacity>
<contents unit="LBS"> 3500 </contents>
</tank>
<tank type="FUEL">
<location unit="IN">
<x> 446.478 </x>
<y> 0 </y>
<z> -18.6033 </z>
</location>
<capacity unit="LBS"> 7000 </capacity>
<contents unit="LBS"> 3500 </contents>
</tank>
</propulsion>
<flight_control name="FCS: F22">
<channel name="Throttle">
<pure_gain name="Throttle1">
<input>fcs/throttle-cmd-norm</input>
<gain>2</gain>
<output>fcs/throttle-pos-norm</output>
</pure_gain>
</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>
</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>
</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 0.0
3.00 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>
</channel>
<channel name="Flaps">
<switch name="Flap Command">
<default value="0"/>
<test logic="OR" value="1">
velocities/vc-kts lt 250
</test>
</switch>
<kinematic name="Flaps Control">
<input>fcs/flap-command</input>
<traverse>
<setting>
<position>0</position>
<time>0</time>
</setting>
<setting>
<position>15</position>
<time>4</time>
</setting>
<setting>
<position>30</position>
<time>3</time>
</setting>
</traverse>
<output>fcs/flap-pos-deg</output>
</kinematic>
<aerosurface_scale name="Flap Position Normalizer">
<input>fcs/flap-pos-deg</input>
<domain>
<min>0</min>
<max>30</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="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>
<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 1.3893
0.1000 1.2108
0.1500 1.1972
0.2000 1.2108
0.3000 1.1785
0.4000 1.0697
0.5000 1.0578
0.6000 1.0323
0.7000 1.0136
0.8000 1.0051
0.9000 1.0017
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</product>
</function>
<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 0.5235
0.1000 0.4759
0.1500 0.5250
0.2000 0.5388
0.3000 0.5924
0.4000 0.6471
0.5000 0.6941
0.6000 0.7624
0.7000 0.8253
0.8000 0.8812
0.9000 0.9412
1.0000 1.0000
1.1000 1.0000
</tableData>
</table>
</product>
</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>
<property>aero/function/kCDge</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-1.5700 1.5000
-0.2600 0.0480
0.0000 0.0240
0.2600 0.0480
1.5700 1.5000
</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>0.0900</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0000
0.8100 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>0.0750</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>0.0200</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>0.0240</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/function/kCDge</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>
<property>fcs/elevator-pos-norm</property>
<property>aero/function/kCDge</property>
<value>0.0750</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>-0.2875</value>
</product>
</function>
<function name="aero/coefficient/CYbdot">
<description>Side_force_due_to_beta_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/betadot-rad_sec</property>
<value>-0.0458</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>0.0619</value>
</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/p-aero-rad_sec</property>
<value>0.0399</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>0.1218</value>
</product>
</function>
</axis>
<axis name="LIFT">
<function name="aero/coefficient/CLalpha">
<description>Lift_due_to_alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.1745 -0.4279
0.7854 2.0000
1.3963 1.0726
</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>
<value>2.5602</value>
</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/function/kCLge</property>
<property>aero/ci2vel</property>
<value>2.7711</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>
<value>0.3500</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>0.0000</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>aero/function/kCLge</property>
<property>fcs/elevator-pos-rad</property>
<value>0.2000</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>
<property>aero/beta-rad</property>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.0873 0.0189
0.0000 0.0176
0.0873 0.0119
0.1745 0.0050
0.2618 0.0049
0.3491 0.0028
0.4363 0.0084
0.5236 0.0171
0.6109 0.0044
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Clbdot">
<description>Roll_moment_due_to_beta_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/ci2vel</property>
<property>aero/betadot-rad_sec</property>
<value>-0.0037</value>
</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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
0.0000 -0.4000
0.3490 -0.3100
</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-aero-rad_sec</property>
<value>0.1500</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.0000 0.0489
2.0000 0.0400
</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>aero/alpha-rad</independentVar>
<tableData>
-0.1745 0.0078
-0.0873 0.0070
0.0000 0.0059
0.0873 0.0043
0.1745 0.0023
0.2618 0.0007
0.3491 -0.0008
0.4363 0.0004
0.5236 0.0019
0.6109 0.0019
0.6981 0.0017
0.7854 0.0009
0.8727 0.0003
1.0472 0.0000
1.2217 0.0000
1.3963 0.0000
</tableData>
</table>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/CmDh">
<description>Pitch_moment_due_to_horizontal_tail_deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/elevator-pos-rad</independentVar>
<tableData>
-0.5236 0.0 0.4363
-0.0873 0.3222 -0.0546 -0.4911
0.0000 0.3482 0.0000 -0.4729
0.0873 0.3897 0.0286 -0.4782
0.1745 0.3689 0.0156 -0.4988
0.2618 0.3975 0.0546 -0.4287
0.3491 0.3819 0.0442 -0.2722
0.4363 0.4131 0.0831 -0.1637
0.5236 0.4599 0.1377 -0.0546
0.6109 0.4443 0.1325 -0.0530
0.6981 0.3819 0.1013 -0.0650
0.7854 0.3585 0.0909 -0.0624
0.8727 0.3430 0.1299 -0.0364
1.0472 0.0208 -0.1117 -0.1975
1.2217 0.3248 -0.4521 -0.5144
</tableData>
</table>
</product>
</function>
<!--
<function name="aero/coefficient/CmDtv">
<description>Pitch_moment_due_to_thrust_vectoring</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>fcs/throttle-pos-norm</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/thrust-control-pos-rad</independentVar>
<tableData>
-0.3491 0.0 0.3491
-0.0873 0.4417 0.0 -0.7924
0.0000 0.4650 0.0 -0.8366
0.0873 0.4448 0.0 -0.8808
0.1745 0.4677 0.0 -0.8886
0.2618 0.4755 0.0 -0.8600
0.3491 0.4625 0.0 -0.6834
0.4363 0.4963 0.0 -0.6001
0.5236 0.4936 0.0 -0.5508
0.6109 0.4781 0.0 -0.5300
0.6981 0.5025 0.0 -0.4754
0.7854 0.5015 0.0 -0.4443
0.8727 0.4209 0.0 -0.4884
1.0472 0.4417 0.0 -0.4547
1.2217 -0.2988 0.0 -0.4183
</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>-17.830</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>
<table>
<independentVar>velocities/mach</independentVar>
<tableData>
0.2570 -1.5611
1.8000 -2.0500
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmadotDh">
<description>Pitch_moment_due_to_horizontal_tail_deflection</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>
<property>fcs/elevator-pos-rad</property>
<value>-1.5611</value>
</product>
</function>
<function name="aero/coefficient/CmqDh">
<description>Pitch_moment_due_to_pitch_rate_and_horizontal_tail_deflection</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>
<property>fcs/elevator-pos-rad</property>
<value>-1.1726</value>
</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>
<value>0.1200</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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.0873 0.0016
0.0000 0.0016
0.0873 0.0018
0.1745 0.0026
0.2618 0.0028
0.3491 0.0026
0.4363 0.0021
0.5236 0.0033
0.6109 0.0015
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnbdot">
<description>Yaw_moment_due_to_beta_rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/ci2vel</property>
<property>aero/betadot-rad_sec</property>
<value>-0.0115</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>-0.0035</value>
</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-aero-rad_sec</property>
<value>-0.1500</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>
<table>
<independentVar>aero/alpha-rad</independentVar>
<tableData>
-0.1745 -0.0082
-0.0873 -0.0128
0.0000 -0.0131
0.0873 -0.0140
0.1745 -0.0154
0.2618 -0.0128
0.3491 -0.0100
0.4363 -0.0077
0.5236 -0.0065
0.6109 -0.0051
0.6981 -0.0041
0.7854 -0.0025
0.8727 0.0000
1.0472 0.0000
1.2217 0.0000
1.3963 0.0000
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/Cnda">
<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>0.0000</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>