Path: ACPro/Airbreathing
% Jet engine model producing thrust and specific fuel consumption.
The default data structure has the afterburner off. The default
fuel is kerosene.
Type Turbojet for a demo.
The demo is for the F135 engine.
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Form:
[t, iSp, tS] = Turbojet( m, d, p )
d = Turbojet;
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Inputs
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m (1,:) Mach number
d (1,1) Data structure for engine
.gamma (1,1) Specific heat ratio of air
.cP (1,1) Specific heat of air
.qR (1,1) Heating value of the fuel
.tT4 (1,1) Temperature at station 4
.tT7 (1,1) Temperature at station 7 (afterburner)
.aInlet (1,1) Inlet area (m^2)
p (1,1) Standard atmosphere
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Outputs
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t (1,:) Thrust (N)
iSp (1,:) Specific impulse (s)
tS (1,:) Specific thrust (N/kg/s)
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Reference: Kerrebrock, J.L, "Aircraft Engines and Gas Turbines", MIT
Press, 1992, pp. 36-39
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AerospaceUtils: AeroData/AtmData Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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