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WIP-jsbsim.xml
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WIP-jsbsim.xml
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<?xml version="1.0" encoding="utf-8"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="panthera" 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 3.3.10</author>
<filecreationdate>26 Sep 2018</filecreationdate>
<version>$Revision: 1.80 $</version>
<description>Models a panthera.</description>
</fileheader>
<!--
File: panthera-jsbsim.xml
Inputs:
name: panthera
type: Single engine WWII Fighter, Military Trainer, Aerobatic, Air Racer
stall speed: 65.00kts
max weight: 2899.57 lb
length: 26.48 ft
wing:
span: 35.63 ft
area: 120.56 sq-ft
mean chord: 4.67 ft
aspect ratio: 6.70:1
taper ratio: 1.00:1
incidence: 2.00 degrees
dihedral: 0.00 degrees
sweep: 0.00 degrees
no. engines: 1
engine type: Piston Engine
engine layout: forward fuselage
gear type: tricycle
steering type: steering
retractable?: yes
Outputs:
wing loading: 24.05 lb/sq-ft
- thickness ratio: 5.60%
payload: 748.75 lbs
CL-alpha: 10.88 per radian
CL-0: 0.37
CL-max: 1.68
CD-0: 0.02
K: 0.06
Mcrit: 0.75
min. turn radius 206.51 ft
max. turn rate: 0.58 deg/s
-->
<metrics>
<wingarea unit="FT2"> 120.56 </wingarea>
<wingspan unit="FT" > 35.63 </wingspan>
<wing_incidence unit="DEG"> 2.00 </wing_incidence>
<chord unit="FT" > 4.67 </chord>
<htailarea unit="FT2"> 18.51 </htailarea>
<htailarm unit="FT" > 17.59 </htailarm>
<vtailarea unit="FT2"> 10.23 </vtailarea>
<vtailarm unit="FT" > 16.40 </vtailarm>
<location name="AERORP" unit="M">
<x> -1.4229 </x>
<y> 0.00 </y>
<z> -0.47766 </z>
</location>
<location name="EYEPOINT" unit="M">
<x> -1.4</x>
<y> -0.3 </y>
<z> 0.25 </z>
</location>
<location name="VRP" unit="IN">
<x> 0.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 1291.24 </ixx>
<iyy unit="SLUG*FT2"> 1267.57 </iyy>
<izz unit="SLUG*FT2"> 2373.34 </izz>
<emptywt unit="LBS" > 1797.07 </emptywt>
<location name="CG" unit="M">
<x> -1.52 </x>
<y> 0.00 </y>
<z> -0.47504 </z>
</location>
<pointmass name="Payload">
<description> 748.75 LBS should bring model up to entered max weight</description>
<weight unit="LBS"> 374.38 </weight>
<location name="POINTMASS" unit="M">
<x> -1.3086 </x>
<y> 0.00 </y>
<z> -0.05502 </z>
</location>
</pointmass>
</mass_balance>
<propulsion>
<engine file="IO-540V">
<location unit="M">
<x> -3.5 </x>
<y> 0.00 </y>
<z> -0.17979 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
<feed> 0 </feed>
<thruster file="my_propeller">
<sense> 1 </sense>
<location unit="M">
<x> -3.84409 </x>
<y> 0.00 </y>
<z> -0.17979 </z>
</location>
<orient unit="DEG">
<pitch> 0.00 </pitch>
<roll> 0.00 </roll>
<yaw> 0.00 </yaw>
</orient>
</thruster>
</engine>
<!--Fuel tanks: 2*105l = 2*173.15lbs-->
<tank type="FUEL" number="0">
<location unit="M">
<x> -1.34541 </x>
<y> -1 </y>
<z> -0.46981 </z>
</location>
<capacity unit="LBS"> 173.15 </capacity>
<contents unit="LBS"> 88.44 </contents>
</tank>
<tank type="FUEL" number="1">
<location unit="M">
<x> -1.34541 </x>
<y> 1 </y>
<z> -0.46981 </z>
</location>
<capacity unit="LBS"> 173.15 </capacity>
<contents unit="LBS"> 88.44 </contents>
</tank>
</propulsion>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="M">
<x> -2.96093 </x>
<y> 0.00 </y>
<z> -1.35345 </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"> 5000 </spring_coeff> <!--869.87-->
<damping_coeff unit="LBS/FT/SEC"> 1300 </damping_coeff> <!--434.94 -->
<max_steer unit="DEG"> 5.00 </max_steer>
<brake_group> NONE </brake_group>
<retractable> 1 </retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="M">
<x> -1.25622 </x>
<y> -1.10162 </y>
<z> -1.35453 </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"> 2899.57 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1449.79 </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="M">
<x> -1.25622 </x>
<y> 1.10162 </y>
<z> -1.35453 </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"> 2899.57 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 1449.79 </damping_coeff>
<max_steer unit="DEG">0</max_steer>
<brake_group> RIGHT </brake_group>
<retractable> 1 </retractable>
</contact>
<contact type="STRUCTURE" name="LEFT_WING">
<location unit="IN">
<x> 106.69 </x>
<y> -213.78 </y>
<z> -7.94 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 2899.57 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2899.57 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x> 106.69 </x>
<y> 213.78 </y>
<z> -7.94 </z>
</location>
<static_friction> 1 </static_friction>
<dynamic_friction> 1 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 2899.57 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 2899.57 </damping_coeff>
</contact>
</ground_reactions>
<system file="conventional-controls.xml" />
<system file="landing-gear.xml" />
<system file="flaps.xml" />
<flight_control name="FCS: panthera"></flight_control>
<aerodynamics>
<axis name="LIFT">
<function name="aero/force/Lift_propwash">
<description>Delta lift due to propeller induced velocity</description>
<product>
<property>propulsion/engine[0]/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 60.0
-0.64 0.000 0.000
0.00 0.080 0.213
0.12 0.362 0.967
0.25 0.000 0.000
</tableData>
</table>
</product>
</function>
<!-- Lift above 0.85 and below -0.85 is generalised -->
<function name="aero/force/Lift_alpha">
<description>Lift due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<tableData>
-1.57 0.0000
-1.22 -0.6068
-1.05 -0.8175
-0.88 -0.9440
-0.63 -0.5243
-0.15 -1.3108
0.00 0.3707
0.12 1.6815
0.60 0.8950
0.88 1.0560
1.05 0.9145
1.22 0.6788
1.57 0.0000
</tableData>
</table>
</product>
</function>
<function name="aero/force/Lift_pitch_rate">
<description>Lift due to pitch rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>velocities/q-aero-rad_sec</property>
<property>aero/ci2vel</property>
<value> 4.7692 </value>
</product>
</function>
<function name="aero/force/Lift_alpha_rate">
<description>Lift due to alpha rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/alphadot-rad_sec</property>
<property>aero/ci2vel</property>
<value> 2.1927 </value>
</product>
</function>
<function name="aero/force/Lift_elevator">
<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> 0.4119 </value>
</product>
</function>
<function name="aero/force/Lift_flap">
<description>Delta Lift due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.0092 </value>
</product>
</function>
</axis>
<axis name="DRAG">
<!-- CD0 is based on fuselage, wing, horizontal- en vertical tail -->
<!-- Antennas, struts and wires are not taken into account -->
<!-- CD for gear (fixed and retractable) is defined below -->
<function name="aero/force/Drag_minimum">
<description>Minimum drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<value> 0.0220 </value>
</product>
</function>
<function name="aero/force/Drag_alpha">
<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>
<tableData>
-1.57 1.4098
-0.12 0.0462
0.00 0.0000
0.12 0.0462
1.57 1.4098
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_induced">
<description>Induced drag</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/cl-squared</property>
<value> 0.0475 </value>
</product>
</function>
<function name="aero/force/Drag_mach">
<description>Drag due to mach</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar lookup="row">velocities/mach</independentVar>
<tableData>
0.00 0.0000
0.75 0.0000
1.10 0.0230
1.80 0.0150
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_beta">
<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 1.2300
-0.26 0.0500
0.00 0.0000
0.26 0.0500
1.57 1.2300
</tableData>
</table>
</product>
</function>
<function name="aero/force/Drag_elevator">
<description>Drag due to Elevator Deflection</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<abs>
<property>fcs/elevator-pos-rad</property>
</abs>
<value> 0.0400 </value>
</product>
</function>
<function name="aero/force/Drag_gear">
<description>Drag due to gear</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>gear/gear-pos-norm</property>
<value> 0.0300 </value>
</product>
</function>
<function name="aero/force/Drag_flap">
<description>Drag due to flaps</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/flap-pos-deg</property>
<value> 0.0012 </value>
</product>
</function>
</axis>
<axis name="SIDE">
<function name="aero/force/Side_beta">
<description>Side force due to beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/beta-rad</property>
<value> -0.3988 </value>
</product>
</function>
<function name="aero/force/Side_roll_rate">
<description>Side force due to roll rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<table>
<independentVar lookup="row">aero/Re</independentVar>
<tableData>
3261546 0.3141
3587700 0.0276
4892318 0.0123
6509190 0.0069
</tableData>
</table>
</product>
</function>
<function name="aero/force/Side_yaw_rate">
<description>Side force due to yaw rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<value> 0.3672 </value>
</product>
</function>
<function name="aero/force/Side_rudder">
<description>Side force due to rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>fcs/rudder-pos-rad</property>
<value> 0.1193 </value>
</product>
</function>
</axis>
<axis name="PITCH">
<function name="aero/moment/Pitch_propwash">
<description>Pitch moment due to propeller induced velocity</description>
<product>
<property>propulsion/engine[0]/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">fcs/flap-pos-deg</independentVar>
<tableData>
0.0 60.0
-0.01 0.000 0.000
0.00 -0.046 -0.123
0.12 -0.210 -0.560
0.16 0.000 0.000
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_alpha">
<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> -0.5000 </value>
</product>
</function>
<function name="aero/moment/Pitch_elevator">
<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 -1.0000
2.0 -0.2500
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Pitch_damp">
<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> -15.0000 </value>
</product>
</function>
<function name="aero/moment/Pitch_alphadot">
<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> -7.0000 </value>
</product>
</function>
</axis>
<axis name="ROLL">
<function name="aero/moment/Roll_differential_propwash">
<description>Roll moment due to differential propwash</description>
<product>
<property>propulsion/engine[0]/thrust-coefficient</property>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/alpha-rad</property>
<value> 0.3590 </value>
</product>
</function>
<function name="aero/moment/Roll_beta">
<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>
<property>fcs/gear-no-wow</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
3261546 3587700 4892318 6509190
-0.0349 -0.1964 -0.0280 -0.0190 -0.0159
0.3491 -0.1964 -0.0280 -0.0190 -0.0159
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_damp">
<description>Roll moment due to roll rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/p-aero-rad_sec</property>
<value> -1.6125 </value>
</product>
</function>
<function name="aero/moment/Roll_yaw">
<description>Roll moment due to yaw rate</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/bi2vel</property>
<property>velocities/r-aero-rad_sec</property>
<table>
<independentVar lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
3261546 3587700 4892318 6509190
-0.0349 -0.0126 -0.0126 -0.0126 -0.0126
0.3491 4.1934 1.0316 1.0316 1.0316
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_aileron">
<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 lookup="row">velocities/mach</independentVar>
<tableData>
0.0 0.1800
2.0 0.0450
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Roll_rudder">
<description>Roll moment due to rudder</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>fcs/rudder-pos-rad</property>
<value> 0.0100 </value>
</product>
</function>
</axis>
<axis name="YAW">
<!-- Stall initiator -->
<function name="aero/moment/Yaw_alpha">
<description>Yaw moment due to alpha</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<property>metrics/bw-ft</property>
<property>aero/alpha-rad</property>
<property>fcs/gear-no-wow</property>
<table>
<independentVar lookup="row">aero/beta-rad</independentVar>
<independentVar lookup="column">aero/Re</independentVar>
<tableData>
3261546 3587700
-0.3491 -1.0000 0.0000
0.3491 1.0000 0.0000
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_beta">
<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> 0.0882 </value>
</product>
</function>
<function name="aero/moment/Yaw_roll_rate">
<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 lookup="row">aero/Re</independentVar>
<tableData>
3261546 -0.1446
3587700 -0.0127
4892318 -0.0056
6509190 -0.0032
</tableData>
</table>
</product>
</function>
<function name="aero/moment/Yaw_damp">
<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> -0.0960 </value>
</product>
</function>
<function name="aero/moment/Yaw_rudder">
<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> -0.0549 </value>
</product>
</function>
<function name="aero/moment/Yaw_aileron">
<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> -0.0030 </value>
</product>
</function>
</axis>
</aerodynamics>
<external_reactions></external_reactions>
</fdm_config>