/
dhc6jsb.xml
881 lines (831 loc) · 39.7 KB
/
dhc6jsb.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="DHC-6" version="2.0" release="BETA"
xmlns:xsi="http://www.w3.org/2001/XMLSchema-instance"
xsi:noNamespaceSchemaLocation="http://jsbsim.sourceforge.net/JSBSim.xsd">
<!--
File: DHC6jsb_Erik.xml
Inputs:
Name: DHC66jsb Erik
Type: Multi engine prop transport
Stall speed: 74 kts
Max weight: 12500 lbs
Length: 51.75 ft
Wing:
Span: 65.00 ft
Area: 420 sq-ft
Mean chord: 6.47 ft
Aspect ratio: 10.1:1
Taper ratio: 0.99:1
Incidence: 2.50 degrees
Dihedral: 3.00 degrees
Sweep: 0.00 degrees
No. engines: 2
Engine type: Turboprop Engine
Engine layout: wings
Control type: Conventional Controls
Gear type: tricycle
Steering type: steering
Retractable: no
Outputs:
Wing loading: 29.59 lb/sq-ft
Thickness ratio: 17.25%
Payload: 5085 lbs = 12500 lbs MOTW minus 7415 lbs empty mass
CL-alpha: 5.81 per radian
CL-0: 0.33
CL-max: 1.60
CD-0: 0.02
K: 0.04
Mcrit: 0.72
-->
<fileheader>
<author> Erik Hofman, Jonathan Schellhase </author>
<filecreationdate> 2003-01-01 </filecreationdate>
<version> $Id: DHC6.xml,v 1.24 2016/11/29 17:38:48 ehofman Exp $ </version>
<description> Flight model configuration for a De Havilland Canada DHC-6-300 Twin Otter </description>
<reference title="http://www.aoc.noaa.gov/aircraft_otter.htm"/>
<reference title="Smart Icing Systems Aerodynamics group UIUC
https://gitorious.org/fg/fgdata/source/73c7e296676c55a4d1db43b49c3fcb938e991177:Aircraft-uiuc/TwinOtter"/>
<reference title="Current Methods for Modeling and Simulating Icing Effects on Aircraft Performance, Stability and Control
http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20090005992_2009004916.pdf"/>
<reference title="Simulation Model Development for Icing Effects Flight Training
http://www.bihrle.aero/pdfs/aiaa2002-01-1527.pdf"/>
<reference title="Performance data of the DHC-6-300
http://www.caamsllc.com/Performance%20Data/DHC-6-300.pdf"/>
<reference title="Linearized mathematical models for De Havilland Canada 'Buffalo & Twin Otter STOL transports
http://www.dtic.mil/dtic/tr/fulltext/u2/733756.pdf"/>
<reference title="STOL RIDE CONTROL FEASIBILITY STUDY Technical Report
https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19730018299.pdf"/>
<reference title="The DHC-6 Twin Otter Specificationa
http://www.719skvadron.no/dhc6/dhc6-spec.htm"/>
<reference title="Manual-TwinOtter-Extended-Vol4-Data
http://www.aerosoft2.de/downloads/twotter/Manual-Twin-Otter-Extended-Vol4-Data.pdf"/>
<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.
</note>
</fileheader>
<metrics>
<wingarea unit="FT2"> 420.00 </wingarea>
<wingspan unit="FT"> 65.00 </wingspan>
<wing_incidence> 2.50 </wing_incidence>
<chord unit="FT"> 6.50 </chord>
<htailarea unit="FT2"> 98.18 </htailarea>
<htailarm unit="FT"> 24.75 </htailarm>
<vtailarea unit="FT2"> 76.05 </vtailarea>
<vtailarm unit="FT"> 11.00 </vtailarm>
<location name="AERORP" unit="IN">
<x> 225.7 </x>
<y> 0.0 </y>
<z> 47.0 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 93.6 </x>
<y> -18.2 </y>
<z> 31.2 </z>
</location>
<location name="VRP" unit="IN">
<x> 249.9 </x>
<y> 0.0 </y>
<z> 7.4 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 16500 </ixx>
<iyy unit="SLUG*FT2"> 26600 </iyy>
<izz unit="SLUG*FT2"> 39800 </izz>
<emptywt unit="LBS"> 7415 </emptywt>
<location name="CG" unit="IN">
<x> 215.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<pointmass name="Crew">
<weight unit="LBS"> 350 </weight>
<location name="POINTMASS" unit="IN">
<x> 126.0 </x>
<y> 0.0 </y>
<z> 10.0 </z>
</location>
</pointmass>
<pointmass name="Forward passengers">
<weight unit="LBS"> 800 </weight>
<location name="POINTMASS" unit="IN">
<x> 188.4 </x>
<y> 2.0 </y>
<z> 6.0 </z>
</location>
</pointmass>
<pointmass name="Rear passengers">
<weight unit="LBS"> 1200 </weight>
<location name="POINTMASS" unit="IN">
<x> 294.0 </x>
<y> 5.0 </y>
<z> 6.0 </z>
</location>
</pointmass>
<pointmass name="Baggage">
<weight unit="LBS"> 500 </weight>
<location name="POINTMASS" unit="IN">
<x> 384.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE_LG">
<location unit="IN">
<x> 73.9 </x>
<y> 0.0 </y>
<z> -63.2 </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"> 8000.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 994.2 </damping_coeff>
<max_steer unit="DEG"> 60.0 </max_steer>
<brake_group> NONE </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="BOGEY" name="LEFT_MLG">
<location unit="IN">
<x> 252.9 </x>
<y> -74.0 </y>
<z> -64.7 </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"> 15000.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1988.4 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> LEFT </brake_group>
<retractable> 0 </retractable>
</contact>
<contact type="BOGEY" name="RIGHT_MLG">
<location unit="IN">
<x> 252.9 </x>
<y> 74.0 </y>
<z> -64.7 </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"> 15000.0 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1988.4 </damping_coeff>
<max_steer unit="DEG"> 0.0 </max_steer>
<brake_group> RIGHT </brake_group>
<retractable> 0 </retractable>
</contact>
</ground_reactions>
<propulsion>
<engine file="PT6A-27">
<location unit="IN">
<x> 142.40 </x>
<y> -109.30 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
<feed>2</feed>
<thruster file="HARTZELL-T10282H">
<location unit="IN">
<x> 142.40 </x>
<y> -109.30 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<engine file="PT6A-27">
<location unit="IN">
<x> 142.40 </x>
<y> 109.30 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
<feed>3</feed>
<thruster file="HARTZELL-T10282H">
<location unit="IN">
<x> 142.40 </x>
<y> 109.30 </y>
<z> -2.88 </z>
</location>
<orient unit="DEG">
<roll> 0.0 </roll>
<pitch> 0.0 </pitch>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<!-- Tank number 0: forward tank -->
<tank type="FUEL" number="0">
<location unit="IN">
<x> 168.00 </x>
<y> 0.00 </y>
<z> -20.40 </z>
</location>
<capacity unit="LBS"> 1233.20 </capacity>
<contents unit="LBS"> 700.00 </contents>
<density unit="LBS/GAL"> 6.74 </density>
<type> JET-A1 </type>
</tank>
<!-- Tank number 1: rear tank -->
<tank type="FUEL" number="1">
<location unit="IN">
<x> 288.00 </x>
<y> 0.00 </y>
<z> -20.40 </z>
</location>
<capacity unit="LBS"> 1349.80 </capacity>
<contents unit="LBS"> 700.00 </contents>
<density unit="LBS/GAL"> 6.74 </density>
<type> JET-A1 </type>
</tank>
<!-- Virtual collector tank (left engine) -->
<tank type="FUEL" number="2">
<location unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 0.10 </capacity>
<contents unit="LBS"> 0.00 </contents>
<density unit="LBS/GAL"> 6.74 </density>
<type> JET-A1 </type>
</tank>
<!-- Virtual collector tank (right engine) -->
<tank type="FUEL" number="3">
<location unit="IN">
<x> 0 </x>
<y> 0 </y>
<z> 0 </z>
</location>
<capacity unit="LBS"> 0.10 </capacity>
<contents unit="LBS"> 0.00 </contents>
<density unit="LBS/GAL"> 6.74 </density>
<type> JET-A1 </type>
</tank>
</propulsion>
<system file="Propulsion.xml"/>
<system file="Conventional_Controls.xml"/>
<system file="Landing_Gear.xml"/>
<system file="Flaps.xml"/>
<system file="Fuel.xml"/>
<system file="Engine.xml"/>
<flight_control name="FCS: DHC-6 Twin Otter">
<!-- Flight control system is defined in "Systems/Conventional Controls" -->
</flight_control>
<aerodynamics>
<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 1.6590
-0.2600 0.0580
0.0000 0.0488
0.2600 0.0580
1.5700 1.6590
</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>
<value>0.0390</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
0.7000 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>
<value>0.0350</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>0.0280</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/mag-beta-rad</independentVar>
<tableData>
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>
<value>0.0350</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>-0.6000</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>0.1500</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>-0.2000</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>0.4000</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>
-0.3491 -0.5800
-0.2618 -0.5200
-0.1745 -0.4500
-0.1396 -0.2800
-0.1047 -0.2000
-0.0698 0.1600
-0.0349 0.3200
0.0000 0.4400
0.0349 0.5800
0.0698 0.7500
0.1047 0.8100
0.1396 0.9500
0.1745 1.1000
0.2094 1.1250
0.2443 1.1400
0.2793 1.1600
0.3142 1.1200
0.3491 1.1300
0.4363 1.1700
0.5236 1.2099
0.6109 1.2699
0.6981 1.3999
</tableData>
</table>
</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>
<table>
<independentVar>fcs/flap-pos-deg</independentVar>
<tableData>
0.0000 0.0000
10.0000 0.9250
20.0000 1.1890
30.0000 1.4750
40.0000 1.6330
</tableData>
</table>
</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>fcs/elevator-pos-rad</property>
<value>0.6080</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/ci2vel</property>
<value>19.9700</value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/coefficient/Clb">
<description>Roll_moment_due_to_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<independentVar lookup="column">aero/alpha-rad</independentVar>
<tableData>
0.0698 0.1745 0.2443 0.3491
-0.3491 0.1250 0.0450 0.0240 -0.0270
-0.2618 0.0900 0.0220 0.0030 -0.0150
-0.1745 0.0770 0.0200 -0.0100 0.0000
-0.0873 0.0360 0.0270 -0.0220 -0.0080
0.0000 0.0000 -0.0100 0.0200 -0.0060
0.0873 0.0360 -0.0170 0.0200 -0.0100
0.1745 0.0770 -0.0100 0.0050 -0.0100
0.2618 0.0900 -0.0250 -0.0180 0.0000
0.3491 0.1250 -0.0450 -0.0350 0.0200
</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>-0.5000</value>
<!--
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 20.0 40.0
0.0000 -0.4078 0.2897 0.4123
0.1745 -0.1537 0.1054 0.0251
0.2618 -0.0055 0.0029 0.0057
0.3491 0.0657 -0.0476 -0.0669
</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>0.0600</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 0.1500
2.0000 0.0500
</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>0.0150</value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/coefficient/Cma">
<description>Pitch_moment_due_to_alpha</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>
<tableData>
-0.3491 0.391
-0.2618 0.423
-0.1745 0.288
-0.0873 0.189
0.0000 0.093
0.0873 -0.048
0.1745 -0.200
0.2618 -0.318
0.3491 -0.384
0.4363 -0.397
0.5236 -0.403
0.6109 -0.469
0.6981 -0.532
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmDe">
<description>Pitch_moment_due_to_elevator_and_flaps</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>
<independentVar lookup="table">fcs/flap-pos-deg</independentVar>
<tableData breakPoint="0.0">
-0.4538 -0.2269 0.0000 0.1222 0.2443
-0.3491 0.2800 0.1700 0.0000 -0.1000 -0.2200
-0.2618 0.2000 0.0900 0.0000 -0.0900 -0.2800
-0.1745 0.4300 0.3100 0.0000 -0.1700 -0.3700
-0.1396 0.5100 0.3700 0.0000 -0.1900 -0.3800
-0.1047 0.5300 0.3900 0.0000 -0.2000 -0.3800
-0.0698 0.5600 0.4000 0.0000 -0.2000 -0.3900
-0.0349 0.5900 0.4100 0.0000 -0.2000 -0.3800
0.0000 0.6300 0.4000 0.0000 -0.1900 -0.3800
0.0349 0.6400 0.3900 0.0000 -0.2000 -0.3600
0.0698 0.6500 0.4000 0.0000 -0.1900 -0.3400
0.1047 0.6400 0.3800 0.0000 -0.1800 -0.3200
0.1396 0.5800 0.3600 0.0000 -0.1600 -0.3200
0.1745 0.5900 0.3700 0.0000 -0.2100 -0.3200
0.2094 0.5600 0.3500 0.0000 -0.2100 -0.3400
0.2443 0.5400 0.3400 0.0000 -0.1900 -0.2900
0.2793 0.4800 0.3300 0.0000 -0.1700 -0.2600
0.3142 0.4300 0.3100 0.0000 -0.1500 -0.2300
0.3491 0.4600 0.3000 0.0000 -0.2100 -0.2000
0.4363 0.2600 0.2100 0.0000 -0.0800 -0.1400
0.5236 0.2900 0.1900 0.0000 -0.0900 -0.1900
0.6109 0.3800 0.2400 0.0000 -0.0800 -0.1600
0.6981 0.4200 0.2300 0.0000 -0.0900 -0.1800
</tableData>
<tableData breakPoint="20.0">
-0.4538 -0.2269 0.0000 0.1222 0.2443
-0.3491 0.3300 0.1800 0.0000 -0.4000 -0.1900
-0.2618 0.3000 0.2100 0.0000 -0.2000 -0.2200
-0.1745 0.4400 0.2400 0.0000 -0.1500 -0.3800
-0.1396 0.4800 0.2800 0.0000 -0.1700 -0.3600
-0.1047 0.4700 0.3000 0.0000 -0.1700 -0.3500
-0.0698 0.4600 0.3200 0.0000 -0.1900 -0.3700
-0.0349 0.4500 0.3500 0.0000 -0.2000 -0.3900
0.0000 0.5300 0.3600 0.0000 -0.2000 -0.4000
0.0349 0.5700 0.3800 0.0000 -0.2000 -0.3800
0.0698 0.5900 0.3900 0.0000 -0.2000 -0.3600
0.1047 0.6200 0.3800 0.0000 -0.2000 -0.3500
0.1396 0.5700 0.3500 0.0000 -0.1500 -0.2900
0.1745 0.4900 0.2900 0.0000 -0.1300 -0.2800
0.2094 0.4700 0.2700 0.0000 -0.1200 -0.2700
0.2443 0.4500 0.2500 0.0000 -0.1300 -0.2700
0.2793 0.4100 0.2300 0.0000 -0.1400 -0.2800
0.3142 0.4200 0.2500 0.0000 -0.1200 -0.3100
0.3491 0.4100 0.2300 0.0000 -0.1500 -0.2700
0.4363 0.3200 0.1900 0.0000 -0.0900 -0.1300
0.5236 0.2400 0.2000 0.0000 -0.0600 -0.1300
0.6109 0.2700 0.1600 0.0000 -0.0800 -0.1700
0.6981 0.3600 0.2100 0.0000 -0.0700 -0.1500
</tableData>
<tableData breakPoint="40.0">
-0.4538 -0.2269 0.0000 0.1222 0.2443
-0.3491 0.2900 0.1700 0.0000 -0.0700 -0.2200
-0.2618 0.2000 0.0900 0.0000 -0.0700 -0.2600
-0.1745 0.1800 0.2100 0.0000 -0.1600 -0.3200
-0.1396 0.3600 0.2900 0.0000 -0.1800 -0.3600
-0.1047 0.4800 0.3300 0.0000 -0.2000 -0.3800
-0.0698 0.5000 0.3600 0.0000 -0.2000 -0.3800
-0.0349 0.5300 0.3700 0.0000 -0.2000 -0.3600
0.0000 0.5600 0.3800 0.0000 -0.1900 -0.3400
0.0349 0.6000 0.3900 0.0000 -0.1700 -0.2900
0.0698 0.6400 0.2600 0.0000 -0.1500 -0.2600
0.1047 0.5900 0.2400 0.0000 -0.1300 -0.2400
0.1396 0.5300 0.2400 0.0000 -0.1100 -0.2000
0.1745 0.4200 0.2200 0.0000 -0.1000 -0.2100
0.2094 0.4100 0.2100 0.0000 -0.1100 -0.2400
0.2443 0.4400 0.2200 0.0000 -0.1300 -0.2300
0.2793 0.4200 0.2500 0.0000 -0.1100 -0.2000
0.3142 0.4800 0.2800 0.0000 -0.1000 -0.2000
0.3491 0.1800 0.2100 0.0000 -0.0800 -0.1900
0.4363 0.2400 0.1900 0.0000 -0.1200 -0.1600
0.5236 0.2800 0.1800 0.0000 -0.0700 -0.1400
0.6109 0.3600 0.1800 0.0000 -0.1000 -0.1700
0.6981 0.3900 0.2100 0.0000 -0.0900 -0.1300
</tableData>
</table>
</product>
</function>
<function name="aero/coefficient/CmT">
<description>Pitch_moment_due_to_propulsion</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/cbarw-ft</property>
<property>systems/propulsion/thrust-coefficient</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.00 40.00
-0.3491 0.0000 0.0000
-0.2618 0.0025 0.0941
-0.1745 0.0187 0.1523
-0.0873 0.0739 0.0898
0.0000 0.0791 0.1691
0.0873 0.1150 0.5529
0.1745 0.2268 0.6156
0.2618 0.3468 0.0000
0.3491 0.2793 0.0000
0.4363 0.0000 0.0000
</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>-34.2000</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>-8.0000</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>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 20.0 40.0
-0.3491 -0.6000 -0.6000 -0.6000
-0.2618 -0.5150 -0.5150 -0.5150
-0.1745 -0.4750 0.0000 0.5923
-0.0873 0.0010 0.5897 1.4987
0.0000 0.5000 1.2032 2.4329
0.0873 0.8670 1.0046 2.8111
0.1745 1.1575 2.2389 3.1892
0.2618 1.1768 2.4895 2.8321
0.3491 1.0080 2.1187 2.5586
0.4363 1.1973 1.9986 2.1203
0.5236 1.1249 1.7488 1.9943
0.6109 1.2786 1.7401 1.8735
0.6981 1.4377 1.7387 1.7387
</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-aero-rad_sec</property>
<value>-0.1800</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>-0.0600</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>-0.1250</value>
</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>-0.0010</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>