Updates from JSBSim, including the new aircraft models: 737 (David Culp), t38 (David Culp), and the p51d (Jon Berndt)
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tony
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6 changed files with 345 additions and 0 deletions
45
Engine/CFM56.xml
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45
Engine/CFM56.xml
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<?xml version="1.0"?>
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<!-- CFM56 turbofan engine model
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Version 0.9, 31 Jan 2003, David Culp, davidculp2@attbi.com
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_______________________________________________________________
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-->
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<FG_TURBINE NAME="CFM56">
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<!-- max static thrust at S.L. (installed), lbs -->
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MAXMILTHRUST 19000
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<!-- augmentation not installed -->
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MAXAUGTHRUST 19000
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<!-- Idle Thrust -->
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<TABLE NAME="IdleThrust" TYPE="TABLE">
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Idle_power_thrust_factor
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6
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 0.0836 0.0528 0.0694 0.0899 0.1183 0.1467
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0.2 0.0501 0.0335 0.0544 0.0797 0.1049 0.1341
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0.4 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
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0.6 -0.0804 -0.0560 -0.0237 0.0276 0.0718 0.1073
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0.8 -0.2129 -0.1498 -0.1025 -0.0195 0.0473 0.0868
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1.0 -0.2839 -0.1104 -0.0469 -0.0270 -0.0158 0.0552
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</TABLE>
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<TABLE NAME="MilThrust" TYPE="TABLE">
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Effects_of_altitude_and_mach_on_thrust
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7
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.0000 0.7216 0.4890 0.3115 0.1932 0.1104
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0.2 1.0000 0.7216 0.4979 0.3186 0.1948 0.1104
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0.4 0.9945 0.7344 0.5213 0.3383 0.2050 0.1230
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0.6 0.9968 0.7759 0.5591 0.3675 0.2240 0.1309
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0.8 0.9771 0.8025 0.6112 0.4196 0.2563 0.1522
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0.9 0.9300 0.7900 0.6000 0.3900 0.2300 0.1300
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1.0 0.5000 0.5000 0.4000 0.2000 0.1500 0.0900
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</TABLE>
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</FG_TURBINE>
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13
Engine/CFM56_nozzle.xml
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13
Engine/CFM56_nozzle.xml
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@ -0,0 +1,13 @@
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<?xml version="1.0"?>
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<FG_NOZZLE NAME="CFM56 Nozzle">
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<!--
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PE = Nozzle exit pressure, psf.
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EXPR = Nozzle expansion ratio, Ae/At, sqft.
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NZL_EFF = Nozzle efficiency, 0.0 - 1.0
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DIAM = Nozzle diameter, ft.
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-->
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EXPR 1.0
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NZL_EFF 1.0
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DIAM 3.0
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</FG_NOZZLE>
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107
Engine/CFM56_sim.xml
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107
Engine/CFM56_sim.xml
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@ -0,0 +1,107 @@
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<?xml version="1.0"?>
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<!-- CFM56 turbofan engine model
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Version 1.0, 14 Mar 2003, David Culp, davidculp2@attbi.com
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-->
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<FG_SIMTURBINE NAME="CFM56">
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<!--
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MAXMILTHRUST max static thrust at S.L. (installed), lbf
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BYPASSRATIO bypass ratio
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TSFC thrust-specific fuel consumption (lbm/hr/lbf)
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ATSFC augmented TSFC (lbm/hr/lbf)
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IDLEN1 idle percent rpm of fan spool
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IDLEN2 idle percent rpm of inner spool
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MAXN1 N1 at 100% throttle
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MAXN2 N2 at 100% throttle
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AUGMENTED =1 if augmentation installed, else =0
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INJECTED =1 if water injection installed, else =0
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TABLE(0) idle thrust vs. altitude and mach
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TABLE(1) maximum un-augmented thrust vs. altitude and mach
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TABLE(2) augmented thrust multiplier vs. altitude and mach
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TABLE(3) water-injection multiplier vs. altitude and mach
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-->
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MAXMILTHRUST 20000
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BYPASSRATIO 5.9
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TSFC 0.657
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ATSFC 0.0
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IDLEN1 30.0
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IDLEN2 60.0
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MAXN1 100.0
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MAXN2 100.0
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AUGMENTED 0
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INJECTED 0
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<TABLE NAME="IdleThrust" TYPE="TABLE">
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Idle_power_thrust_factor
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6
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 0.0836 0.0528 0.0694 0.0899 0.1183 0.1467
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0.2 0.0501 0.0335 0.0544 0.0797 0.1049 0.1341
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0.4 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
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0.6 -0.0804 -0.0560 -0.0237 0.0276 0.0718 0.1073
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0.8 -0.2129 -0.1498 -0.1025 -0.0195 0.0473 0.0868
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1.0 -0.2839 -0.1104 -0.0469 -0.0270 -0.0158 0.0552
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</TABLE>
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<TABLE NAME="MilThrust" TYPE="TABLE">
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Effects_of_altitude_and_mach_on_thrust
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7
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.0000 0.7216 0.4890 0.3115 0.1932 0.1104
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0.2 1.0000 0.7216 0.4979 0.3186 0.1948 0.1104
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0.4 0.9945 0.7344 0.5213 0.3383 0.2050 0.1230
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0.6 0.9968 0.7759 0.5591 0.3675 0.2240 0.1309
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0.8 0.9771 0.8025 0.6112 0.4196 0.2563 0.1522
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0.9 0.9300 0.7900 0.6000 0.3900 0.2300 0.1300
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1.0 0.5000 0.5000 0.4000 0.2000 0.1500 0.0900
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</TABLE>
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<TABLE NAME="AugThrust" TYPE="TABLE">
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Augmented_thrust_factor
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8
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.6 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.8 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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1.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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1.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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1.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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</TABLE>
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<TABLE NAME="WaterFactor" TYPE="TABLE">
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Water_Injection_factor
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8
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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0.2 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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0.4 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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0.6 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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0.8 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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1.0 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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1.2 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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1.4 1.2000 1.2000 1.2000 1.2000 1.2000 1.2000
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</TABLE>
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</FG_SIMTURBINE>
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58
Engine/J85-GE-5.xml
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58
Engine/J85-GE-5.xml
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<?xml version="1.0"?>
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<!-- J85-GE-5 afterburning turbojet engine model -->
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<FG_TURBINE NAME="J85">
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<!-- max static thrust at S.L. (installed), lbs -->
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MAXMILTHRUST 2050
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<!-- max augmented thrust at S.L. (installed), lbs -->
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MAXAUGTHRUST 2900
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<!-- Idle Thrust -->
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<TABLE NAME="IdleThrust" TYPE="TABLE">
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Idle_power_thrust_factor
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6
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 0.0836 0.0528 0.0694 0.0899 0.1183 0.1467
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0.2 0.0501 0.0335 0.0544 0.0797 0.1049 0.1341
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0.4 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
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0.6 -0.0804 -0.0560 -0.0237 0.0276 0.0718 0.1073
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0.8 -0.2129 -0.1498 -0.1025 -0.0195 0.0473 0.0868
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1.0 -0.2839 -0.1104 -0.0469 -0.0270 -0.0158 0.0552
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</TABLE>
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<TABLE NAME="MilThrust" TYPE="TABLE">
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Military_power_thrust_factor
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6
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.0000 0.7216 0.4890 0.3115 0.1932 0.1104
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0.2 1.0000 0.7216 0.4979 0.3186 0.1948 0.1104
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0.4 0.9945 0.7344 0.5213 0.3383 0.2050 0.1230
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0.6 0.9968 0.7759 0.5591 0.3675 0.2240 0.1309
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0.8 0.9771 0.8025 0.6112 0.4196 0.2563 0.1522
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1.0 0.9211 0.7767 0.6349 0.4811 0.2997 0.1822
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</TABLE>
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<TABLE NAME="AugThrust" TYPE="TABLE">
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Augmented_thrust
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8
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 0.6924 0.5193 0.3739 0.2423 0.1385 0.0865
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0.2 0.7415 0.5435 0.3886 0.2535 0.1535 0.0900
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0.4 0.7858 0.5837 0.4241 0.2823 0.1731 0.0981
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0.6 0.8392 0.6546 0.4764 0.3214 0.1973 0.1113
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0.8 0.9025 0.7296 0.5530 0.3848 0.2375 0.1367
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1.0 1.0000 0.8073 0.6335 0.4668 0.2992 0.1751
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1.2 1.0000 0.9000 0.7000 0.5300 0.4000 0.0200
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1.4 1.0000 0.9000 0.8000 0.6000 0.5000 0.0200
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</TABLE>
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</FG_TURBINE>
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109
Engine/J85-GE-5_sim.xml
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109
Engine/J85-GE-5_sim.xml
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@ -0,0 +1,109 @@
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<?xml version="1.0"?>
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<!--
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J85-GE-5 afterburning turbojet engine
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for the JSBSim SimTurbine model
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-->
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<FG_SIMTURBINE NAME="J85">
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<!--
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MAXMILTHRUST max static thrust at S.L. (installed), lbf
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BYPASSRATIO bypass ratio
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TSFC thrust-specific fuel consumption (lbm/hr/lbf)
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ATSFC augmented TSFC (lbm/hr/lbf)
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IDLEN1 idle percent rpm of fan spool
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IDLEN2 idle percent rpm of inner spool
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MAXN1 N1 at 100% throttle
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MAXN2 N2 at 100% throttle
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AUGMENTED =1 if augmentation installed
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INJECTED =1 if water injection installed
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TABLE(0) idle thrust vs. altitude and mach
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TABLE(1) maximum un-augmented thrust vs. altitude and mach
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TABLE(2) augmented thrust multiplier vs. altitude and mach
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TABLE(3) water-injection multiplier vs. altitude and mach
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-->
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MAXMILTHRUST 2050
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BYPASSRATIO 0
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TSFC 1.1219
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ATSFC 2.5172
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IDLEN1 0.0
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IDLEN2 49.2
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MAXN1 0.0
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MAXN2 100.0
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AUGMENTED 1
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INJECTED 0
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<TABLE NAME="IdleThrust" TYPE="TABLE">
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Idle_power_thrust_factor
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6
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 0.0836 0.0528 0.0694 0.0899 0.1183 0.1467
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0.2 0.0501 0.0335 0.0544 0.0797 0.1049 0.1341
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0.4 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
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0.6 -0.0804 -0.0560 -0.0237 0.0276 0.0718 0.1073
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0.8 -0.2129 -0.1498 -0.1025 -0.0195 0.0473 0.0868
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1.0 -0.2839 -0.1104 -0.0469 -0.0270 -0.0158 0.0552
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</TABLE>
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<!-- data from EngineSim, http://www.grc.nasa.gov/WWW/K-12/airplane/ngnsim.html -->
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<TABLE NAME="MilThrust" TYPE="TABLE">
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Military_power_thrust_factor
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8
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490
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0.2 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430
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0.4 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450
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0.6 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540
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0.8 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700
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1.0 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950
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1.2 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250
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1.4 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630
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</TABLE>
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<TABLE NAME="AugThrust" TYPE="TABLE">
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Augmented_thrust_factor
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8
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6
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velocities/mach-norm
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position/h-sl-ft
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none
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0 10000 20000 30000 40000 50000
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0.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.6 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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0.8 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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1.0 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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1.2 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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1.4 1.4146 1.4146 1.4146 1.4146 1.4146 1.4146
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</TABLE>
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||||||
|
<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
13
Engine/J85_nozzle.xml
Normal file
|
|
@ -0,0 +1,13 @@
|
||||||
|
<?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>
|
||||||
|
|
||||||
Loading…
Reference in a new issue