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super-tucano-FDM.xml
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super-tucano-FDM.xml
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<?xml version="1.0"?>
<?xml-stylesheet type="text/xsl" href="http://jsbsim.sourceforge.net/JSBSim.xsl"?>
<fdm_config name="tucano" 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 0.9 </author>
<filecreationdate> 2009-01-04 </filecreationdate>
<version>$Revison: $</version>
<description> Models a tucano. </description>
</fileheader>
<!--
File: tucano.xml
Inputs:
name: tucano
type: WWII fighter, subsonic sport, aerobatic
max weight: 7000.875 lb
wing span: 36.55034 ft
length: 32.44909 ft
wing area: unspecified
gear type: tricycle
retractable?: yes
# engines: 1
engine type: turbine
engine layout: forward fuselage
yaw damper? no
Outputs:
wing loading: 45.00 lb/sq-ft
CL-alpha: 4.5 per radian
CL-0: 0.17
CL-max: 1.2
CD-0: 0.02
K: 0.045
-->
<metrics>
<wingarea unit="FT2"> 208.82 </wingarea>
<wingspan unit="FT" > 36.55 </wingspan>
<wing_incidence> 2.00 </wing_incidence>
<chord unit="FT" > 5.71 </chord>
<htailarea unit="FT2"> 26.45 </htailarea>
<htailarm unit="FT" > 19.47 </htailarm>
<vtailarea unit="FT2"> 15.56 </vtailarea>
<vtailarm unit="FT" > 19.47 </vtailarm>
<location name="AERORP" unit="IN">
<x> 162.00 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<location name="EYEPOINT" unit="IN">
<x> 109.03 </x>
<y> 0.00 </y>
<z> 40.00 </z>
</location>
<location name="VRP" unit="IN">
<x>163</x>
<y>0</y>
<z>0</z>
</location>
</metrics>
<mass_balance>
<ixx unit="SLUG*FT2"> 5176 </ixx>
<iyy unit="SLUG*FT2"> 7450 </iyy>
<izz unit="SLUG*FT2"> 9847 </izz>
<emptywt unit="LBS" > 6658 </emptywt>
<location name="CG" unit="IN">
<x> 163.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<pointmass name="station1"><!-- missle -->
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> -114 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="station2"><!-- empty tank -->
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> -100 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="station3"><!-- empty center tank -->
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> -0 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="station4"><!-- empty tank def 75 -->
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> 100 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="station5"><!-- missle def 150-->
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> 114 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="Pilot"><!-- pilot -->
<weight unit="LBS"> 165 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> -0 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="Co-pilot"><!-- co-pilot -->
<weight unit="LBS"> 165 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> -0 </y>
<z> 0 </z>
</location>
</pointmass>
<pointmass name="Equipment"><!-- equipments -->
<weight unit="LBS"> 0 </weight>
<location name="POINTMASS" unit="IN">
<x> 163 </x>
<y> -0 </y>
<z> 0 </z>
</location>
</pointmass>
</mass_balance>
<ground_reactions>
<contact type="BOGEY" name="NOSE">
<location unit="IN">
<x> 39.0 </x>
<y> 0.0 </y>
<z> -71.0 </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>
<damping_coeff unit="LBS/FT/SEC"> 2500 </damping_coeff>
<max_steer unit="DEG"> 55.00 </max_steer>
<brake_group>NONE</brake_group>
<retractable>1</retractable>
</contact>
<contact type="BOGEY" name="LEFT_MAIN">
<location unit="IN">
<x> 171.0 </x>
<y> -66.0 </y>
<z> -74.0 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.60 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 9000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4400 </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> 171.0 </x>
<y> 66.0 </y>
<z> -74.0 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.60 </dynamic_friction>
<rolling_friction> 0.02 </rolling_friction>
<spring_coeff unit="LBS/FT"> 9000 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 4400 </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> 170 </x>
<y>-230 </y>
<z> 0 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 7000.88 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7400.18 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="RIGHT_WING">
<location unit="IN">
<x> 170 </x>
<y> 230 </y>
<z> 0 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 7000.88 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7400.18 </damping_coeff>
</contact>
<contact type="STRUCTURE" name="TAIL">
<location unit="IN">
<x> 430 </x>
<y> 0 </y>
<z> -8 </z>
</location>
<static_friction> 0.80 </static_friction>
<dynamic_friction> 0.50 </dynamic_friction>
<spring_coeff unit="LBS/FT"> 7000.88 </spring_coeff>
<damping_coeff unit="LBS/FT/SEC"> 7400.18 </damping_coeff>
</contact>
</ground_reactions>
<external_reactions>
<force name="pushback" frame="BODY">
<location unit="IN">
<x>39.0</x>
<y>0.0</y>
<z>-71.0</z>
</location>
<direction>
<x>1</x>
<y>0</y>
<z>0</z>
</direction>
</force>
</external_reactions>
<propulsion>
<engine file="PT6A-68C">
<location unit="IN">
<x> 30.00 </x>
<y> 0.00 </y>
<z> 0.00 </z>
</location>
<feed>0</feed>
<feed>1</feed>
<feed>2</feed>
<feed>3</feed>
<thruster file="direct">
<location unit="IN">
<x> 26.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<orient unit="DEG">
<pitch> 0.0 </pitch>
<roll> 0.0 </roll>
<yaw> 0.0 </yaw>
</orient>
</thruster>
</engine>
<tank type="FUEL" number="0"><!-- Internal fuel, 630 liters -->
<location unit="IN">
<x> 170.0 </x>
<y> 0.0 </y>
<z> 0.0 </z>
</location>
<priority>2</priority>
<density unit="LBS/GAL"> 6.48 </density>
<capacity unit="LBS"> 1112.00 </capacity>
<contents unit="LBS"> 1100.00 </contents>
</tank>
<tank type="FUEL" number="1"><!-- Left external tank, 320 liters -->
<location unit="IN">
<x> 170.0 </x>
<y> -98.0 </y>
<z> -6.0 </z>
</location>
<density unit="LBS/GAL"> 6.48 </density>
<capacity unit="LBS"> 566.00 </capacity>
<contents unit="LBS"> 0 </contents>
</tank>
<tank type="FUEL" number="2"><!-- Right external tank, 320 liters -->
<location unit="IN">
<x> 170.0 </x>
<y> 98.0 </y>
<z> -6.0 </z>
</location>
<density unit="LBS/GAL"> 6.48 </density>
<capacity unit="LBS"> 566.00 </capacity>
<contents unit="LBS"> 0 </contents>
</tank>
<tank type="FUEL" number="3"><!-- Center external tank, 320 liters -->
<location unit="IN">
<x> 170.0 </x>
<y> 0.0 </y>
<z> -6.0 </z>
</location>
<density unit="LBS/GAL"> 6.48 </density>
<capacity unit="LBS"> 566.00 </capacity>
<contents unit="LBS"> 0 </contents>
</tank>
</propulsion>
<system file="gear"/>
<system file="flaps"/>
<system file="FCS-pitch"/>
<system file="FCS-roll"/>
<system file="FCS-yaw"/>
<system file="NWS"/>
<system file="alpha_buffet"/>
<system file="crash-detect"/>
<system file="speedbrakes"/>
<system file="canopy"/>
<system file="particles"/>
<system file="fuel"/>
<system file="pushback"/>
<flight_control name="FCS: tucano"/>
<aerodynamics>
<hysteresis_limits unit="RAD">
<min>0.00</min>
<max>0.36</max>
</hysteresis_limits>
<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 0.0480
0.1000 0.5150
0.1500 0.6290
0.2000 0.7090
0.3000 0.8150
0.4000 0.8820
0.5000 0.9280
0.6000 0.9620
0.7000 0.9880
0.8000 1.0000
</tableData>
</table>
</product>
</function>
<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="LIFT">
<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 lookup="row">aero/alpha-rad</independentVar>
<independentVar lookup="column">aero/stall-hyst-norm</independentVar>
<tableData>
0 1
-0.20 -0.73 -0.73
0.00 0.17 0.17
0.23 1.10 0.70
0.36 0.70 0.70
0.60 0.20 0.20
</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>
<property>fcs/flap-pos-norm</property>
<value> 0.18 </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>0.15</value>
</product>
</function>
<function name="aero/coefficient/buffet">
<description>Buffet at high alpha</description>
<product>
<property>systems/alpha_buffet/sine_wave</property>
<property>systems/alpha_buffet/strength</property>
</product>
</function>
</axis>
<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 lookup="row">aero/alpha-rad</independentVar>
<tableData>
-1.57 1.500
-0.26 0.026
0.00 0.021
0.26 0.026
1.57 1.500
</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>0.05</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 lookup="row">velocities/mach</independentVar>
<tableData>
0.00 0.000
0.75 0.000
1.10 0.023
1.80 0.015
</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> 0.039 </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>0.035</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 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/CDde">
<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>0.035</value>
</product>
</function>
<function name="aero/coefficient/dCDprop">
<description>Drag_due_to_prop_beta</description>
<product>
<property>aero/qbar-psf</property>
<property>metrics/Sw-sqft</property>
<table>
<independentVar>fcs/throttle-pos-norm</independentVar>
<tableData>
0.0000 0.0700
0.0500 0.0000
1.0000 0.0000
</tableData>
</table>
</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>0.016</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>-1</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>
<value>-0.1</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>
<value>-0.4</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>0.15</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>0.11</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>0.011</value>
</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>
<value>-0.5</value>
</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">aero/alpha-rad</independentVar>
<tableData>
0.23 -0.80
0.27 -0.80
0.30 0
</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>-15</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>-7</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>0.12</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>-0.15</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>-0.08</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>-0.002</value>
</product>
</function>
</axis>
</aerodynamics>
</fdm_config>