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Add David Culp's North American OV-10A Bronco and T-6A Texan II aircraft

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This commit is contained in:
ehofman 2003-05-22 10:05:44 +00:00
parent 8c9d1b4ca7
commit d6b41a3e3b
7 changed files with 318 additions and 2 deletions
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41
Aircraft/OV10-jsbsim-set.xml Normal file
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<?xml version="1.0"?>
<!--
************************************************************************
OV-10 JSBSim config file
David Culp, davidculp2@attbi.com
************************************************************************
-->
<PropertyList>
<sim>
<description>North American OV-10A Bronco</description>
<flight-model>jsb</flight-model>
<aero>OV10</aero>
<systems>
<electrical>
<path>Aircraft/T38/T38-electrical.xml</path>
</electrical>
</systems>
<sound>
<audible>true</audible>
<path>Aircraft/OV10/Sounds/OV10-sound.xml</path>
</sound>
<panel>
<path>Aircraft/T38/Panels/T38-panel.xml</path>
<visibility archive="y">true</visibility>
</panel>
<model>
<path>Aircraft/OV10/Models/OV10.mdl</path>
</model>
-->
</sim>
</PropertyList>

7
Aircraft/OV10-set.xml Normal file
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<?xml version="1.0"?>
<PropertyList include="OV10-jsbsim-set.xml">
<sim>
<description>Alias for OV10-jsbsim.</description>
</sim>
</PropertyList>

4
Aircraft/a4-yasim-set.xml
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@ -1,7 +1,7 @@
<?xml version="1.0"?>
<!--
************************************************************************
British Aerospace A4 Hawksimulation config. This files ties together
Douglas A4 Skyhawk simulation config. This files ties together
all the components used by FGFS to represent the A4. Components include
the flight data model, instrument panel, and external 3D model.
@ -11,7 +11,7 @@ the flight data model, instrument panel, and external 3D model.
<PropertyList>
<sim>
<description>British Aerospace A4 Hawk (YASim)</description>
<description>Douglas A4 Skyhawk (YASim)</description>
<virtual-cockpit archive="y">true</virtual-cockpit>

41
Aircraft/t6texan2-jsbsim-set.xml Normal file
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<?xml version="1.0"?>
<!--
************************************************************************
T-6A Texan-II JSBSim config file
David Culp, davidculp2@attbi.com
************************************************************************
-->
<PropertyList>
<sim>
<description>T-6A Texan II</description>
<flight-model>jsb</flight-model>
<aero>t6texan2</aero>
<systems>
<electrical>
<path>Aircraft/c172/c172-electrical.xml</path>
</electrical>
</systems>
<sound>
<audible>true</audible>
<path>Aircraft/t6texan2/Sounds/t6texan2-sound.xml</path>
</sound>
<panel>
<path>Aircraft/T38/Panels/T38-panel.xml</path>
<visibility archive="y">true</visibility>
</panel>
<model>
<path>Aircraft/t6texan2/Models/T6Texan2.mdl</path>
</model>
</sim>
</PropertyList>

7
Aircraft/t6texan2-set.xml Normal file
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<?xml version="1.0"?>
<PropertyList include="t6texan2-jsbsim-set.xml">
<sim>
<description>Alias for t6texan2-jsbsim.</description>
</sim>
</PropertyList>

110
Engine/PT6A-68_sim.xml Normal file
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<?xml version="1.0"?>
<!-- PT6A-68 turboprop engine model
for the SimTurbine turbine model -->
<FG_SIMTURBINE NAME="PT6A-68">
<!--
MAXMILTHRUST max static thrust at S.L. (installed), lbf
BYPASSRATIO bypass ratio
TSFC thrust-specific fuel consumption (lbm/hr/lbf)
ATSFC augmented TSFC (lbm/hr/lbf)
IDLEN1 idle percent rpm of fan spool
IDLEN2 idle percent rpm of inner spool
MAXN1 N1 at 100% throttle
MAXN2 N2 at 100% throttle
AUGMENTED = 1 if augmentation installed, else = 0
AUGMETHOD = 0 if using property /engine[n]/augmentation
= 1 if using last 1% of throttle movement
INJECTED = 1 if water injection installed
TABLE(0) idle thrust vs. altitude and mach
TABLE(1) maximum un-augmented thrust vs. altitude and mach
TABLE(2) augmented thrust multiplier vs. altitude and mach
TABLE(3) water-injection multiplier vs. altitude and mach
-->
MAXMILTHRUST 1500
BYPASSRATIO 0
TSFC 0.55
ATSFC 0.00
IDLEN1 0.0
IDLEN2 65.0
MAXN1 0.0
MAXN2 100.0
AUGMENTED 0
AUGMETHOD 0
INJECTED 0
<TABLE NAME="IdleThrust" TYPE="TABLE">
Idle_power_thrust_factor
6
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 0.0836 0.0528 0.0694 0.0899 0.1183 0.1467
0.2 0.0501 0.0335 0.0544 0.0797 0.1049 0.1341
0.4 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
0.6 -0.0804 -0.0560 -0.0237 0.0276 0.0718 0.1073
0.8 -0.2129 -0.1498 -0.1025 -0.0195 0.0473 0.0868
1.0 -0.2839 -0.1104 -0.0469 -0.0270 -0.0158 0.0552
</TABLE>
<!-- data from EngineSim, http://www.grc.nasa.gov/WWW/K-12/airplane/ngnsim.html -->
<TABLE NAME="MilThrust" TYPE="TABLE">
Military_power_thrust_factor
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490
0.2 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430
0.4 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450
0.6 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540
0.8 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700
1.0 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950
1.2 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250
1.4 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630
</TABLE>
<TABLE NAME="AugThrust" TYPE="TABLE">
Augmented_thrust_factor
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.6 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.8 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
1.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
1.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
1.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
</TABLE>
<TABLE NAME="WaterFactor" TYPE="TABLE">
Water_Injection_factor
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.2 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.4 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.6 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.8 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
1.0 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
1.2 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
1.4 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
</TABLE>
</FG_SIMTURBINE>

110
Engine/T76_sim.xml Normal file
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<?xml version="1.0"?>
<!-- T76 turboprop engine model
for the SimTurbine turbine model -->
<FG_SIMTURBINE NAME="T76">
<!--
MAXMILTHRUST max static thrust at S.L. (installed), lbf
BYPASSRATIO bypass ratio
TSFC thrust-specific fuel consumption (lbm/hr/lbf)
ATSFC augmented TSFC (lbm/hr/lbf)
IDLEN1 idle percent rpm of fan spool
IDLEN2 idle percent rpm of inner spool
MAXN1 N1 at 100% throttle
MAXN2 N2 at 100% throttle
AUGMENTED = 1 if augmentation installed, else = 0
AUGMETHOD = 0 if using property /engine[n]/augmentation
= 1 if using last 1% of throttle movement
INJECTED = 1 if water injection installed
TABLE(0) idle thrust vs. altitude and mach
TABLE(1) maximum un-augmented thrust vs. altitude and mach
TABLE(2) augmented thrust multiplier vs. altitude and mach
TABLE(3) water-injection multiplier vs. altitude and mach
-->
MAXMILTHRUST 1200
BYPASSRATIO 0
TSFC 0.55
ATSFC 0.00
IDLEN1 0.0
IDLEN2 61.0
MAXN1 0.0
MAXN2 100.0
AUGMENTED 0
AUGMETHOD 0
INJECTED 0
<TABLE NAME="IdleThrust" TYPE="TABLE">
Idle_power_thrust_factor
6
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 0.0836 0.0528 0.0694 0.0899 0.1183 0.1467
0.2 0.0501 0.0335 0.0544 0.0797 0.1049 0.1341
0.4 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
0.6 -0.0804 -0.0560 -0.0237 0.0276 0.0718 0.1073
0.8 -0.2129 -0.1498 -0.1025 -0.0195 0.0473 0.0868
1.0 -0.2839 -0.1104 -0.0469 -0.0270 -0.0158 0.0552
</TABLE>
<!-- data from EngineSim, http://www.grc.nasa.gov/WWW/K-12/airplane/ngnsim.html -->
<TABLE NAME="MilThrust" TYPE="TABLE">
Military_power_thrust_factor
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490
0.2 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430
0.4 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450
0.6 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540
0.8 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700
1.0 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950
1.2 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250
1.4 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630
</TABLE>
<TABLE NAME="AugThrust" TYPE="TABLE">
Augmented_thrust_factor
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.6 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
0.8 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
1.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
1.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
1.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
</TABLE>
<TABLE NAME="WaterFactor" TYPE="TABLE">
Water_Injection_factor
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.2 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.4 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.6 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
0.8 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
1.0 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
1.2 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
1.4 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
</TABLE>
</FG_SIMTURBINE>