<?xml version="1.0" ?>
<!--
  File:     Olympus593Mrk610.xml
  Author:   Aero-Matic v 0.7
  Version:  1.05
  Date:     1st January 2008

  Inputs:
    name:           Olympus593Mrk610
    type:           turbine
    thrust:         31350 lb
    augmented?      yes
    injected?       no


  References :
  ==========
    - http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
    (FAA certificate, E20eu - 15 january 1981, Olympus).

    - http://www.airweb.faa.gov/Regulatory_and_Guidance_Library/rgMakeModel.nsf/MainFrame?OpenFrameSet
    (FAA certificate, A45eu - 9 january 1979, Concorde) :

                               Static         N1 (low       N2 (high                  Time
    Condition                thrust (lb)    compressor)    compressor)      EGT       limit
    .........................................................................................
    Start and relight             -              -              -          550�C      2 s
    Contingency                 38130           102%          106.8%       883�C      2.5 s
    Takeoff (with reheat)       37080           102%          105.7%       806�C      5 minutes
    Takeoff (without reheat)    31350           102%          105.7%       806�C      5 minutes
    Reheated climb              32800           102%          105.1%       755�C      15 minutes
    Maximum continuous          28800           102%          105.3%       736�C      unrestricted
    Idle                          -              -             60% (min)              unrestricted
    Maximum overspeed                           108.5%        110.0%         -        20 s
    Reverse (ground)              -              -             98.0%         -        30 s
    Reverse (flight)              -         (as obtained at reversed idle)   -        4 minutes

    - http://www.concordesst.com :
    Olympus 593 Mrk 610 turbojet (RollsRoyce / SNECMA).
    Maximum thurst at take off (with afterburner reheat) : 38050 lbs (170 KN).
    Maximum thrust produced during supersonic cruise : 10000 lbs.
    Reheat contribution to performance : 20% at full thrust during take off.
    Fuel type : A1 jet fuel.
    Fuel capacity : 26400 gallons, 119500 l, 95680 kg.
    Fuel consumption (at idle power) : 1100 kg/h (302 gallons/h).
    Fuel consumption (at full power) : 10500 kg/h (2885 gallons/h).
    Fuel consumption (at full reheat power) : 22500 kg/h (6180 gallons/h).

    As air intakes move at Mach 1.3, a shockwave forms.
    Takeoff and cruise : 82% of thrust by engine, 6% from nozzle and 12% by intakes.
    Supersonic cruise : 8% of thrust by engine, 29% from nozzle and 63% by intakes.

    - http://www.aircraftenginedesign.com :
    Takeoff : Thrust 38000 lb, Bypass Ratio 0, Overall Pressure Ratio 11.3 (cruise), Airflow : 410 lb/s.
    Cruise  : Altitude : 53000 ft, Mach 2.00, Thrust 10030 lb, TSFC : 1.190.

    - http://www.alpa.org/alpa/DesktopModules/ViewDocument.aspx?DocumentID=814 :
    At Mach 1.3, inlet-guide ramps lower to slow down the intake air.
    At Mach 1.7 the afterburners are turned off, and the non-bypass engines are able to increase
    to Mach 2.04 (1150 kt) with about half the fuel flow.
    At cruise speed, the air entering the engines is reduced by intake ramps to 500 kt.
    This drop in intakes provides 45% of thrust, the engines 50%, and the convergent/divergent effect
    of the nozzle and stowed thrust reversers, 5%.
    At Mach 2.04, fuel flow is 45200 lb/h.

-->
<turbine_engine name="Olympus593Mrk610">
  <!--
     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
  -->

  <!-- - TSFC 10500 kg/h / 31350 lbs = 0.738 :
       Get the right consumption at max thrust (sea level).
       Depends strongly of center of gravity and aero reference point.
       - ATSFC 22500 kg/h / 37080 lbs = 1.338 :
       Get the right consumption at afterburner (sea level).

       Adjust the TSFC to get 20500 kg/h on average, at Mach 2.02 between 50000-57800 ft
      (60 ft/min during 2h10).
  -->

  <milthrust> 31350 </milthrust>
  <maxthrust> 37080 </maxthrust>
  <bypassratio> 0.0 </bypassratio>
  <tsfc> 1.144 </tsfc>                       <!-- 0.738 x 1.55 -->
  <atsfc> 1.338 </atsfc>
  <idlen1> 30.0 </idlen1>
  <idlen2> 60.0 </idlen2>
  <maxn1> 102.0 </maxn1>
  <maxn2> 106.0 </maxn2>
  <augmented> 1 </augmented>
  <augmethod> 0 </augmethod>
  <injected> 0 </injected>

  <!-- At takeoff and subsonic cruise : 12% of thrust by intake, 6% by secondary nozzles
                                        = x 1.1360.
       Air intakes starts at Mach 1.3 : 63 % of thrust in supersonic cruise, 29% secondary nozzles
                                        = x 2.7030.

       One supposes secondary nozzles included in the engine thrust.
       Simplification : no air intake effect above Mach 1.3.


       Ground idle = 90 % of normal thrust.
  -->

 <function name="IdleThrust">
  <table>
   <independentVar lookup="row">velocities/mach</independentVar>
   <independentVar lookup="column">atmosphere/density-altitude</independentVar>
   <independentVar lookup="table">fcs/ground-idle</independentVar>
   <tableData breakPoint="0">
          -10000      0  10000  20000  30000  40000  50000  60000  80000
    0.0   0.0430 0.0488 0.0528 0.0694 0.0899 0.1183 0.1467 0.0792  0.0
    0.2   0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.1342 0.0725  0.0
    0.4   0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203 0.0650  0.0
    0.6   0.0    0.0    0.0    0.0    0.0276 0.0718 0.1073 0.0579  0.0
    0.8   0.0    0.0    0.0    0.0    0.0474 0.0868 0.0900 0.0486  0.0
    1.0   0.0    0.0    0.0    0.0    0.0    0.0552 0.0800 0.0432  0.0
    1.2   0.0    0.0    0.0    0.0    0.0    0.0530 0.0768 0.0415  0.0
    1.4   0.0    0.0    0.0    0.0    0.0    0.0519 0.0753 0.0407  0.0
    1.6   0.0    0.0    0.0    0.0    0.0    0.0    0.0745 0.0403  0.0
    1.8   0.0    0.0    0.0    0.0    0.0    0.0    0.0723 0.0391  0.0
    2.0   0.0    0.0    0.0    0.0    0.0    0.0    0.0680 0.0368  0.0
    2.2   0.0    0.0    0.0    0.0    0.0    0.0    0.0605 0.0328  0.0
   </tableData>
   <tableData breakPoint="1">
          -10000      0  10000  20000  30000  40000  50000  60000  80000
    0.0   0.0387 0.0439 0.0475 0.0625 0.0809 0.1065 0.1320 0.0713  0.0
    0.2   0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.1342 0.0725  0.0
    0.4   0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203 0.0650  0.0
    0.6   0.0    0.0    0.0    0.0    0.0276 0.0718 0.1073 0.0579  0.0
    0.8   0.0    0.0    0.0    0.0    0.0474 0.0868 0.0900 0.0486  0.0
    1.0   0.0    0.0    0.0    0.0    0.0    0.0552 0.0800 0.0432  0.0
    1.2   0.0    0.0    0.0    0.0    0.0    0.0530 0.0768 0.0415  0.0
    1.4   0.0    0.0    0.0    0.0    0.0    0.0519 0.0753 0.0407  0.0
    1.6   0.0    0.0    0.0    0.0    0.0    0.0    0.0745 0.0403  0.0
    1.8   0.0    0.0    0.0    0.0    0.0    0.0    0.0723 0.0391  0.0
    2.0   0.0    0.0    0.0    0.0    0.0    0.0    0.0680 0.0368  0.0
    2.2   0.0    0.0    0.0    0.0    0.0    0.0    0.0605 0.0328  0.0
   </tableData>
  </table>
 </function>

    <!-- Add average (without X factor) at Mach 1.3.

         Above Mach 1.3 :
         - x 1.2 at Mach 1.4.
         - x 1.4 at Mach 1.6.
         - x 1.8 at Mach 1.8.
         - x 2.7 at Mach 2.0.
         - x 2.7 at Mach 2.2.
    -->

 <function name="MilThrust">
  <table>
   <independentVar lookup="row">velocities/mach</independentVar>
   <independentVar lookup="column">atmosphere/density-altitude</independentVar>
   <independentVar lookup="table">fcs/intake-subsonic-pos</independentVar>
   <tableData breakPoint="0">
          -10000      0  10000  20000  30000  40000  50000  60000  80000
    0.0   1.2600 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490 0.0805  0.0
    0.2   1.1710 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430 0.0772  0.0
    0.4   1.1500 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450 0.0783  0.0
    0.6   1.1810 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540 0.0832  0.0
    0.8   1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700 0.0918  0.0
    1.0   1.3690 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950 0.1053  0.0
    1.2   1.4850 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250 0.1215  0.0
    1.3   1.5396 1.2850 1.0305 0.7945 0.5865 0.3940 0.2440 0.1318  0.0
    1.4   1.9129 1.6080 1.3032 1.0140 0.7536 0.5088 0.3156 0.1704  0.0
    1.6   2.0895 1.7636 1.4377 1.1571 0.9142 0.6464 0.4004 0.2202  0.0
    1.8   2.6159 2.2043 1.7928 1.4382 1.1333 0.7997 0.4955 0.2725  0.0
    2.0   3.6096 3.0945 2.5793 2.0644 1.6192 1.1405 0.7066 0.3888  0.0
    2.2   3.4042 2.9203 2.4365 2.1427 1.5725 1.0989 0.6809 0.3745  0.0
   </tableData>
   <tableData breakPoint="1">
          -10000      0  10000  20000  30000  40000  50000  60000  80000
    0.0   1.2600 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490 0.0805  0.0
    0.2   1.1710 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430 0.0772  0.0
    0.4   1.1500 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450 0.0783  0.0
    0.6   1.1810 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540 0.0832  0.0
    0.8   1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700 0.0918  0.0
    1.0   1.3690 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950 0.1053  0.0
    1.2   1.4850 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250 0.1215  0.0
    1.4   1.5941 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630 0.1420  0.0
    1.6   1.4925 1.2597 1.0269 0.8265 0.6530 0.4617 0.2860 0.1573  0.0
    1.8   1.4533 1.2246 0.9960 0.7990 0.6296 0.4443 0.2753 0.1514  0.0
    2.0   1.3369 1.1461 0.9553 0.7646 0.5997 0.4224 0.2617 0.1440  0.0
    2.2   1.2608 1.0816 0.9024 0.7936 0.5824 0.4070 0.2522 0.1387  0.0
   </tableData>
  </table>
 </function>

    <!-- Add average (without X factor ) at Mach 1.3.

         Above Mach 1.3 :
         - x 1.2 at Mach 1.4.
         - x 1.4 at Mach 1.6.
         - x 1.8 at Mach 1.8.
         - x 2.7 at Mach 2.0.
         - x 2.5 at Mach 2.2.
         - burn fuel to match consumption London-New York.
         - avoid overspeed until Mach 1.7.
    -->

  <function name="AugThrust">
   <table>
    <independentVar lookup="row">velocities/mach</independentVar>
    <independentVar lookup="column">atmosphere/density-altitude</independentVar>
    <independentVar lookup="table">fcs/intake-subsonic-pos</independentVar>
    <tableData breakPoint="0">
          -10000      0  10000  20000  30000  40000  50000  60000  80000
    0.0   1.1816 1.0000 0.8184 0.6627 0.5280 0.3756 0.2327 0.1280  0.0
    0.2   1.1308 0.9599 0.7890 0.6406 0.5116 0.3645 0.2258 0.1242  0.0
    0.4   1.1150 0.9474 0.7798 0.6340 0.5070 0.3615 0.2240 0.1232  0.0
    0.6   1.1284 0.9589 0.7894 0.6420 0.5134 0.3661 0.2268 0.1247  0.0
    0.8   1.1707 0.9942 0.8177 0.6647 0.5309 0.3784 0.2345 0.1290  0.0
    1.0   1.2411 1.0529 0.8648 0.7017 0.5596 0.3983 0.2467 0.1357  0.0
    1.2   1.3287 1.1254 0.9221 0.7462 0.5936 0.4219 0.2614 0.1438  0.0
    1.3   1.3826 1.1702 0.9577 0.7742 0.6148 0.4364 0.2704 0.1488  0.0
    1.4   1.7238 1.4579 1.1920 0.9625 0.7632 0.5411 0.3353 0.1846  0.0
    1.6   2.1995 1.8564 1.5132 1.2180 0.9224 0.6804 0.4215 0.2318  0.0
    1.8   3.1142 2.6242 2.1343 1.7122 1.3491 0.9520 0.5899 0.3244  0.0
    2.0   4.9945 4.2390 3.5332 2.8280 2.2183 1.5622 0.9680 0.5324  0.0
    2.2   4.9250 4.2250 3.5250 3.1000 2.2750 1.5898 0.9850 0.5418  0.0
   </tableData>
    <tableData breakPoint="1">
          -10000      0  10000  20000  30000  40000  50000  60000  80000
    0.0   1.1816 1.0000 0.8184 0.6627 0.5280 0.3756 0.2327 0.1280  0.0
    0.2   1.1308 0.9599 0.7890 0.6406 0.5116 0.3645 0.2258 0.1242  0.0
    0.4   1.1150 0.9474 0.7798 0.6340 0.5070 0.3615 0.2240 0.1232  0.0
    0.6   1.1284 0.9589 0.7894 0.6420 0.5134 0.3661 0.2268 0.1247  0.0
    0.8   1.1707 0.9942 0.8177 0.6647 0.5309 0.3784 0.2345 0.1290  0.0
    1.0   1.2411 1.0529 0.8648 0.7017 0.5596 0.3983 0.2467 0.1357  0.0
    1.2   1.3287 1.1254 0.9221 0.7462 0.5936 0.4219 0.2614 0.1438  0.0
    1.4   1.4365 1.2149 0.9933 0.8021 0.6360 0.4509 0.2794 0.1538  0.0
    1.6   1.5711 1.3260 1.0809 0.8700 0.6874 0.4860 0.3011 0.1656  0.0
    1.8   1.7301 1.4579 1.1857 0.9512 0.7495 0.5289 0.3277 0.1802  0.0
    2.0   1.8314 1.5700 1.3086 1.0474 0.8216 0.5786 0.3585 0.1972  0.0
    2.2   1.9700 1.6900 1.4100 1.2400 0.9100 0.6359 0.3940 0.2167  0.0
    2.4   2.0700 1.8000 1.5300 1.3400 1.0000 0.7200 0.4600 0.2530  0.0
    2.6   2.2000 1.9200 1.6400 1.4400 1.1000 0.8000 0.5200 0.2860  0.0
    </tableData>
  </table>
 </function>


<!-- ===================================== -->
<!-- === backup of extrapolated tables === -->
<!-- ===================================== -->

<!--
<TABLE NAME="Idle6Thrust" TYPE="TABLE">

      at 50000 ft :
      - 0.2 X 0.915.
      - 0.4 X 0.896.
      - 0.6 X 0.892.
      - 0.8 X 0.84.
      - 1.0 X 0.89.

      extrapolated (staying below military) :
      - 1.2 X 0.96.
      - 1.4 X 0.98.
      - 1.6 X 0.99 (maximum).
      - 1.8 X 0.97.
      - 2.0 X 0.94.
      - 2.2 X 0.89.

      at Mach 1.0 :
      - 50000 X 1.45.

      at Mach 0.8 :
      - 40000 X 1.83.
      - 50000 X 1.04.

      at Mach 0.6 :
      - 40000 X 2.60.
      - 50000 X 1.50.

      at Mach 0.4 :
      - 30000 X 2.19.
      - 40000 X 1.50.
      - 50000 X 1.35.

      extrapolated (like military) :
      - 60000 X 0.54.

 Idle6_power_thrust_factor
 12 8
 velocities/mach-norm position/h-sl-ft
 none
        -10000      0  10000  20000  30000  40000  50000  60000
 0.0    0.0430 0.0488 0.0528 0.0694 0.0899 0.1183 0.1467 0.0792
 0.2    0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.1342 0.0725
 0.4    0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203 0.0650
 0.6    0.0    0.0    0.0    0.0    0.0276 0.0718 0.1073 0.0579
 0.8    0.0    0.0    0.0    0.0    0.0474 0.0868 0.0900 0.0486
 1.0    0.0    0.0    0.0    0.0    0.0    0.0552 0.0800 0.0432
 1.2    0.0    0.0    0.0    0.0    0.0    0.0530 0.0768 0.0415
 1.4    0.0    0.0    0.0    0.0    0.0    0.0519 0.0753 0.0407
 1.6    0.0    0.0    0.0    0.0    0.0    0.0    0.0745 0.0403
 1.8    0.0    0.0    0.0    0.0    0.0    0.0    0.0723 0.0391
 2.0    0.0    0.0    0.0    0.0    0.0    0.0    0.0680 0.0368
 2.2    0.0    0.0    0.0    0.0    0.0    0.0    0.0605 0.0328
</TABLE> 

<TABLE NAME="Mil6Thrust" TYPE="TABLE">

      at 50000 ft :
      - 0.4 X 1.014.
      - 0.6 X 1.062.
      - 0.8 X 1.104.
      - 1.0 X 1.147.
      - 1.2 X 1.15.
      - 1.4 X 1.17.

      ratio augmented / military at 50000 ft :
      - 0.4 X 1.55.
      - 0.6 X 1.47.
      - 0.8 X 1.38.
      - 1.0 X 1.27.
      - 1.2 X 1.16.
      - 1.4 X 1.06.

      extrapolated from augmented :
      - 1.6 X 0.95.
      - 1.8 X 0.84.
      - 2.0 X 0.73.
      - 2.2 X 0.64

      at Mach 1.4 :
      - 20000 X 0.78.
      - 30000 X 0.74.
      - 40000 X 0.68.
      - 50000 X 0.62.

      extrapolated (staying below augmented) :
      - 60000 X 0.54.

 Military6_power_thrust_factor
 12 8
 velocities/mach-norm position/h-sl-ft
 none 
        -10000      0  10000  20000  30000  40000  50000  60000
 0.0    1.2600 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490 0.0805
 0.2    1.1710 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430 0.0772
 0.4    1.1500 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450 0.0783
 0.6    1.1810 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540 0.0832
 0.8    1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700 0.0918
 1.0    1.3690 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950 0.1053
 1.2    1.4850 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250 0.1215
 1.4    1.5941 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630 0.1420
 1.6    1.4925 1.2597 1.0269 0.8265 0.6530 0.4617 0.2860 0.1573
 1.8    1.4533 1.2246 0.9960 0.7990 0.6296 0.4443 0.2753 0.1514
 2.0    1.3369 1.1461 0.9553 0.7646 0.5997 0.4224 0.2617 0.1440
 2.2    1.2608 1.0816 0.9024 0.7936 0.5824 0.4070 0.2522 0.1387
</TABLE> 

<TABLE NAME="Aug6Thrust" TYPE="TABLE">

      at Mach 2.6 :
      - 20000 X 0.88.
      - 30000 X 0.76.
      - 40000 X 0.73.
      - 50000 X 0.65.

      extrapolated :
      - 60000 X 0.55.

 Augmented6_thrust_factor
 14 8
 velocities/mach-norm position/h-sl-ft
 none
        -10000      0  10000  20000  30000  40000  50000  60000
 0.0    1.1816 1.0000 0.8184 0.6627 0.5280 0.3756 0.2327 0.1280
 0.2    1.1308 0.9599 0.7890 0.6406 0.5116 0.3645 0.2258 0.1242
 0.4    1.1150 0.9474 0.7798 0.6340 0.5070 0.3615 0.2240 0.1232
 0.6    1.1284 0.9589 0.7894 0.6420 0.5134 0.3661 0.2268 0.1247
 0.8    1.1707 0.9942 0.8177 0.6647 0.5309 0.3784 0.2345 0.1290
 1.0    1.2411 1.0529 0.8648 0.7017 0.5596 0.3983 0.2467 0.1357
 1.2    1.3287 1.1254 0.9221 0.7462 0.5936 0.4219 0.2614 0.1438
 1.4    1.4365 1.2149 0.9933 0.8021 0.6360 0.4509 0.2794 0.1538
 1.6    1.5711 1.3260 1.0809 0.8700 0.6874 0.4860 0.3011 0.1656
 1.8    1.7301 1.4579 1.1857 0.9512 0.7495 0.5289 0.3277 0.1802
 2.0    1.8314 1.5700 1.3086 1.0474 0.8216 0.5786 0.3585 0.1972
 2.2    1.9700 1.6900 1.4100 1.2400 0.9100 0.6359 0.3940 0.2167
 2.4    2.0700 1.8000 1.5300 1.3400 1.0000 0.7200 0.4600 0.2530
 2.6    2.2000 1.9200 1.6400 1.4400 1.1000 0.8000 0.5200 0.2860
</TABLE>
--> 


<!-- ========================================================================== -->
<!-- BACKUP of default tables, which are correct : get 10073 lb at Mach 2 FL500 -->
<!-- ========================================================================== -->
 
<!--
  <TABLE NAME="IdleThrust" TYPE="TABLE">
    Idle_power_thrust_factor
    6
    7
    velocities/mach-norm
    position/h-sl-ft
    none
          -10000      0  10000  20000  30000  40000  50000
    0.0   0.0430 0.0488 0.0528 0.0694 0.0899 0.1183 0.1467
    0.2   0.0500 0.0501 0.0335 0.0544 0.0797 0.1049 0.1342
    0.4   0.0040 0.0047 0.0020 0.0272 0.0595 0.0891 0.1203
    0.6   0.0    0.0    0.0    0.0    0.0276 0.0718 0.1073
    0.8   0.0    0.0    0.0    0.0    0.0474 0.0868 0.0900
    1.0   0.0    0.0    0.0    0.0    0.0    0.0552 0.0800
  </TABLE>
 
  <TABLE NAME="MilThrust" TYPE="TABLE">
    Military_power_thrust_factor
    8
    7
    velocities/mach-norm
    position/h-sl-ft
    none
          -10000      0  10000  20000  30000  40000  50000
    0.0   1.2600 1.0000 0.7400 0.5340 0.3720 0.2410 0.1490
    0.2   1.1710 0.9340 0.6970 0.5060 0.3550 0.2310 0.1430
    0.4   1.1500 0.9210 0.6920 0.5060 0.3570 0.2330 0.1450
    0.6   1.1810 0.9510 0.7210 0.5320 0.3780 0.2480 0.1540
    0.8   1.2580 1.0200 0.7820 0.5820 0.4170 0.2750 0.1700
    1.0   1.3690 1.1200 0.8710 0.6510 0.4750 0.3150 0.1950
    1.2   1.4850 1.2300 0.9750 0.7440 0.5450 0.3640 0.2250
    1.4   1.5941 1.3400 1.0860 0.8450 0.6280 0.4240 0.2630
  </TABLE>
 
  <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> 
-->


<!-- emulation (multiplier) by water injection -->

<!--
  <TABLE NAME="AirIntakeThrust" TYPE="TABLE">
         At takeoff and subsonic cruise : 12% of thrust by intake, 6% by secondary nozzles.
         Air intakes starts at Mach 1.3 : 63 % of thrust in supersonic cruise, 29% secondary nozzles.
         One supposes secondary nozzles included in the engine thrust.

    AirIntake_thrust_factor
    3
    7
    velocities/mach-norm
    position/h-sl-ft
    none
          -10000      0  10000  20000  30000  40000  50000
    0.0   1.1360 1.1360 1.1360 1.1360 1.1360 1.1360 1.1360
    1.3   1.1360 1.1360 1.1360 1.1360 1.1360 1.1360 1.1360
    2.04  2.7030 2.7030 2.7030 2.7030 2.7030 2.7030 2.7030
  </TABLE>
-->

</turbine_engine>