jsbsim.js
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JSBSim flight dynamics model ported to JavaScript
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text/xml
<!--
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>