102 lines
4 KiB
XML
102 lines
4 KiB
XML
<?xml version="1.0"?>
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<!-- F100-PW-229 afterburning turbofan engine model
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for the SimTurbine turbine model -->
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<FG_SIMTURBINE NAME="F100">
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<!--
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MILTHRUST max static thrust (without afterburner) at S.L. (installed), lbf
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MAXTHRUST max static thrust with afterburner 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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AUGMETHOD = 0 if using property /engine[n]/augmentation
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= 1 if using last 1% of throttle movement
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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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MILTHRUST 17800
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MAXTHRUST 29000
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BYPASSRATIO 0.4
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TSFC 0.74
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ATSFC 2.05
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IDLEN1 40.0
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IDLEN2 53.0
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MAXN1 100.0
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MAXN2 100.0
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AUGMENTED 1
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AUGMETHOD 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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<!-- data from EngineSim, http://www.grc.nasa.gov/WWW/K-12/airplane/ngnsim.html,
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extrapolated to higher mach numbers -->
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<TABLE NAME="AugThrust" TYPE="TABLE">
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Augmented_thrust_factor
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14
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7
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velocities/mach-norm
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position/h-sl-ft
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none
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-10000 0 10000 20000 30000 40000 50000
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0.0 1.1816 1.0000 0.8184 0.6627 0.5280 0.3756 0.2327
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0.2 1.1308 0.9599 0.7890 0.6406 0.5116 0.3645 0.2258
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0.4 1.1150 0.9474 0.7798 0.6340 0.5070 0.3615 0.2240
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0.6 1.1284 0.9589 0.7894 0.6420 0.5134 0.3661 0.2268
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0.8 1.1707 0.9942 0.8177 0.6647 0.5309 0.3784 0.2345
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1.0 1.2411 1.0529 0.8648 0.7017 0.5596 0.3983 0.2467
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1.2 1.3287 1.1254 0.9221 0.7462 0.5936 0.4219 0.2614
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1.4 1.4365 1.2149 0.9933 0.8021 0.6360 0.4509 0.2794
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1.6 1.5711 1.3260 1.0809 0.8700 0.6874 0.4860 0.3011
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1.8 1.7301 1.4579 1.1857 0.9512 0.7495 0.5289 0.3277
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2.0 1.8314 1.5700 1.3086 1.0474 0.8216 0.5786 0.3585
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2.2 1.9700 1.6900 1.4100 1.2400 0.9100 0.6359 0.3940
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2.4 2.0700 1.8000 1.5300 1.3400 1.0000 0.7200 0.4600
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2.6 2.2000 1.9200 1.6400 1.4400 1.1000 0.8000 0.5200
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</TABLE>
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</FG_SIMTURBINE>
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