fgdata/Engine/F100-PW-229_sim.xml

<?xml version="1.0"?>

<!-- F100-PW-229 afterburning turbofan engine model
     for the SimTurbine turbine model -->

<FG_SIMTURBINE NAME="F100">
  <!--
     MILTHRUST     max static thrust (without afterburner) at S.L. (installed), lbf
     MAXTHRUST     max static thrust with afterburner 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
  -->

  MILTHRUST  17800
  MAXTHRUST  29000
  BYPASSRATIO  0.4
  TSFC         0.74
  ATSFC        2.05
  IDLEN1       40.0
  IDLEN2       53.0
  MAXN1        100.0
  MAXN2        100.0
  AUGMENTED    1
  AUGMETHOD    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>

  <!-- data from EngineSim, http://www.grc.nasa.gov/WWW/K-12/airplane/ngnsim.html,
   extrapolated to higher mach numbers -->
  <TABLE NAME="AugThrust" TYPE="TABLE">
    Augmented_thrust_factor
    14
    7
    velocities/mach-norm
    position/h-sl-ft
    none
           -10000        0    10000   20000     30000    40000    50000
    0.0    1.1816   1.0000   0.8184   0.6627   0.5280   0.3756   0.2327
    0.2    1.1308   0.9599   0.7890   0.6406   0.5116   0.3645   0.2258
    0.4    1.1150   0.9474   0.7798   0.6340   0.5070   0.3615   0.2240
    0.6    1.1284   0.9589   0.7894   0.6420   0.5134   0.3661   0.2268
    0.8    1.1707   0.9942   0.8177   0.6647   0.5309   0.3784   0.2345
    1.0    1.2411   1.0529   0.8648   0.7017   0.5596   0.3983   0.2467
    1.2    1.3287   1.1254   0.9221   0.7462   0.5936   0.4219   0.2614
    1.4    1.4365   1.2149   0.9933   0.8021   0.6360   0.4509   0.2794
    1.6    1.5711   1.3260   1.0809   0.8700   0.6874   0.4860   0.3011
    1.8    1.7301   1.4579   1.1857   0.9512   0.7495   0.5289   0.3277
    2.0    1.8314   1.5700   1.3086   1.0474   0.8216   0.5786   0.3585
    2.2    1.9700   1.6900   1.4100   1.2400   0.9100   0.6359   0.3940
    2.4    2.0700   1.8000   1.5300   1.3400   1.0000   0.7200   0.4600
    2.6    2.2000   1.9200   1.6400   1.4400   1.1000   0.8000   0.5200
  </TABLE>

</FG_SIMTURBINE>