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Path: ACPro/Airbreathing
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Generate an engine table for a matrix of altitudes and mach.
Each row of output is an altitude and each column a Mach number.
Since version 5.
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Form:
[t, sFC] = EngineTable( type, h, m, d, p )
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Inputs
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type (1,:) 'turbofan' or 'ramjet'
h (1,:) Altitude
m (1,:) Mach number
d (1,1) Engine parameter data structure (see EngineExample.m)
p (1,1) Throttle settings (turbofan only)
.afterburner (1,1) Afterburner on == 1
.throttleRatio (1,1) Throttle ratio
.tT4 (1,1) Combustor temperature (K)
.tT7 (1,1) Afterburner temperature (K)
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Outputs
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t (:,:) Thrust (N)
sFC (:,:) Thrust specific fuel consumption
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See also MixedFlowTurbofan, RamjetH2
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ACPro: Airbreathing/EngineExample ACPro: Airbreathing/MixedFlowTurbofan ACPro: Airbreathing/Ramjet Common: Atmosphere/StdAtm Common: Graphics/Plot2D
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