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Path: ACPro/Airbreathing
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Turbofan jet engine model produces thrust and specific fuel consumption.
Type Turbofan for a demo.
The numbers and letters in the code refer to
a ambient
0 stagnation
1 inlet to diffuser
2 inlet to compressor
3 inlet to the burner
4 inlet to the turbine
5 outlet from the turbine and inlet to the afterburner
6 inlet to the nozzle
7 outlet from the nozzle
8 outlet from the fan
Since version 2014.1
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Form:
[t, tSFC, tS, temp] = Turbofan( m, d, q )
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Inputs
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m (n,1) Mach number
d (1,1) Data structure for engine
.gamma (1,1) Specific heat ratio of air
.gamma1 (1,1) Specific heat ratio of combustion gas
.cP (1,1) Specific heat of air
.cP1 (1,1) Specific heat of combustion gas
.etaD (1,1) Diffusor efficiency
.etaF (1,1) Fan efficiency
.etaC (1,1) Compressor efficiency
.etaN (1,1) Nozzle efficiency
.beta (1,1) Bypass ratio
.mDiffusor (1,1) Mach number at the diffusor exit
.qR (1,1) Gas constant of fuel
.t04 (1,1) Combustor exit temperature deg-K
.p08OP0A (1,1) Fan pressure ratio
.p04OP03 (1,1) Pressure ratio across the burner
.p06OP05 (1,1) Pressure ratio across the afterburner
.aInlet (1,1) Inlet area (m^2)
.mDiffusor (1,1) Diffusor Mach number
q (1,1) Standard atmosphere
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Outputs
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t (m,n) Thrust (N)
tSFC (m,n) Specific fuel consumption (kg/s/N)
tS (m,n) Specific thrust (N/kg/s)
temp (m,n,10) Temperatures
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Reference: Hill, P. G. and Peterson, C. R. "Mechanics and
Thermodynamics of Propulsion," Addison Wesley, 1970.
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Common: Atmosphere/StdAtm Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/XLabelS
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