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Updates from JSBSim, including the new aircraft models: 737 (David Culp), t38 (David Culp), and the p51d (Jon Berndt)

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tony 2003-03-23 15:16:40 +00:00
parent 64a3e56366
commit b48c22857b
6 changed files with 345 additions and 0 deletions
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45
Engine/CFM56.xml Normal file
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<?xml version="1.0"?>
<!-- CFM56 turbofan engine model
Version 0.9, 31 Jan 2003, David Culp, davidculp2@attbi.com
_______________________________________________________________
-->
<FG_TURBINE NAME="CFM56">
<!-- max static thrust at S.L. (installed), lbs -->
MAXMILTHRUST 19000
<!-- augmentation not installed -->
MAXAUGTHRUST 19000
<!-- Idle Thrust -->
<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>
<TABLE NAME="MilThrust" TYPE="TABLE">
Effects_of_altitude_and_mach_on_thrust
7
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.0000 0.7216 0.4890 0.3115 0.1932 0.1104
0.2 1.0000 0.7216 0.4979 0.3186 0.1948 0.1104
0.4 0.9945 0.7344 0.5213 0.3383 0.2050 0.1230
0.6 0.9968 0.7759 0.5591 0.3675 0.2240 0.1309
0.8 0.9771 0.8025 0.6112 0.4196 0.2563 0.1522
0.9 0.9300 0.7900 0.6000 0.3900 0.2300 0.1300
1.0 0.5000 0.5000 0.4000 0.2000 0.1500 0.0900
</TABLE>
</FG_TURBINE>

13
Engine/CFM56_nozzle.xml Normal file
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<?xml version="1.0"?>
<FG_NOZZLE NAME="CFM56 Nozzle">
<!--
PE = Nozzle exit pressure, psf.
EXPR = Nozzle expansion ratio, Ae/At, sqft.
NZL_EFF = Nozzle efficiency, 0.0 - 1.0
DIAM = Nozzle diameter, ft.
-->
EXPR 1.0
NZL_EFF 1.0
DIAM 3.0
</FG_NOZZLE>

107
Engine/CFM56_sim.xml Normal file
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<?xml version="1.0"?>
<!-- CFM56 turbofan engine model
Version 1.0, 14 Mar 2003, David Culp, davidculp2@attbi.com
-->
<FG_SIMTURBINE NAME="CFM56">
<!--
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
INJECTED =1 if water injection installed, else =0
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 20000
BYPASSRATIO 5.9
TSFC 0.657
ATSFC 0.0
IDLEN1 30.0
IDLEN2 60.0
MAXN1 100.0
MAXN2 100.0
AUGMENTED 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>
<TABLE NAME="MilThrust" TYPE="TABLE">
Effects_of_altitude_and_mach_on_thrust
7
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.0000 0.7216 0.4890 0.3115 0.1932 0.1104
0.2 1.0000 0.7216 0.4979 0.3186 0.1948 0.1104
0.4 0.9945 0.7344 0.5213 0.3383 0.2050 0.1230
0.6 0.9968 0.7759 0.5591 0.3675 0.2240 0.1309
0.8 0.9771 0.8025 0.6112 0.4196 0.2563 0.1522
0.9 0.9300 0.7900 0.6000 0.3900 0.2300 0.1300
1.0 0.5000 0.5000 0.4000 0.2000 0.1500 0.0900
</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>

58
Engine/J85-GE-5.xml Normal file
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<?xml version="1.0"?>
<!-- J85-GE-5 afterburning turbojet engine model -->
<FG_TURBINE NAME="J85">
<!-- max static thrust at S.L. (installed), lbs -->
MAXMILTHRUST 2050
<!-- max augmented thrust at S.L. (installed), lbs -->
MAXAUGTHRUST 2900
<!-- Idle Thrust -->
<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>
<TABLE NAME="MilThrust" TYPE="TABLE">
Military_power_thrust_factor
6
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 1.0000 0.7216 0.4890 0.3115 0.1932 0.1104
0.2 1.0000 0.7216 0.4979 0.3186 0.1948 0.1104
0.4 0.9945 0.7344 0.5213 0.3383 0.2050 0.1230
0.6 0.9968 0.7759 0.5591 0.3675 0.2240 0.1309
0.8 0.9771 0.8025 0.6112 0.4196 0.2563 0.1522
1.0 0.9211 0.7767 0.6349 0.4811 0.2997 0.1822
</TABLE>
<TABLE NAME="AugThrust" TYPE="TABLE">
Augmented_thrust
8
6
velocities/mach-norm
position/h-sl-ft
none
0 10000 20000 30000 40000 50000
0.0 0.6924 0.5193 0.3739 0.2423 0.1385 0.0865
0.2 0.7415 0.5435 0.3886 0.2535 0.1535 0.0900
0.4 0.7858 0.5837 0.4241 0.2823 0.1731 0.0981
0.6 0.8392 0.6546 0.4764 0.3214 0.1973 0.1113
0.8 0.9025 0.7296 0.5530 0.3848 0.2375 0.1367
1.0 1.0000 0.8073 0.6335 0.4668 0.2992 0.1751
1.2 1.0000 0.9000 0.7000 0.5300 0.4000 0.0200
1.4 1.0000 0.9000 0.8000 0.6000 0.5000 0.0200
</TABLE>
</FG_TURBINE>

109
Engine/J85-GE-5_sim.xml Normal file
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<?xml version="1.0"?>
<!--
J85-GE-5 afterburning turbojet engine
for the JSBSim SimTurbine model
-->
<FG_SIMTURBINE NAME="J85">
<!--
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
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 2050
BYPASSRATIO 0
TSFC 1.1219
ATSFC 2.5172
IDLEN1 0.0
IDLEN2 49.2
MAXN1 0.0
MAXN2 100.0
AUGMENTED 1
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>

13
Engine/J85_nozzle.xml Normal file
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<?xml version="1.0"?>
<FG_NOZZLE NAME="T38 Nozzle">
<!--
PE = Nozzle exit pressure, psf.
EXPR = Nozzle expansion ratio, Ae/At, sqft.
NZL_EFF = Nozzle efficiency, 0.0 - 1.0
DIAM = Nozzle diameter, ft.
-->
EXPR 1.0
NZL_EFF 1.0
DIAM 2.0
</FG_NOZZLE>