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SUPPORT SITE |
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Path: ACPro/ACEngine
% Jet engine analysis. You can vary up to two of the
parameters in p. You can get demos by typing
JetEngineAnalysis( 'Ramjet' ), etc.
If you enter JetEngineAnalysis( 'Ramjet', 1 ) it will echo the d and
p structures.
Engine parameters are in d and given below. You only need to enter
parameters that are relevant to your engine. For example, ramjets
don't require fan and compressor parameters.
Turbojets and turbofans may have afterburners.
This function is used to design engines. Once you have a design
(possibly from an external source) use JetEnginePerformance to
study it at different throttle settings.
Supported engines are:
'Ramjet'
'Turbojet'
'Dual Exhaust Turbofan',
'Mixed Flow Turbofan'
'Turboprop'
--------------------------------------------------------------------------
Form:
[g, d, p, def] = = JetEngineAnalysis( p, d )
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Inputs
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p (1,1) Performance parameters
See def or GasTurbineDefinitions.m
d (1,1) Engine data structure
See def or GasTurbineDefinitions.m
echo (1,1) Just return outputs
-------
Outputs
-------
g (1,1) Output data structure
.fO (n,m) Fuel/air ratio
.etaO (n,m) Overall efficiency
.etaP (n,m) Propulsive efficiency
.etaT (n,m) Thermal efficiency
.fOverMDotA (n,m) Specific force
.s (n,m) Specific fuel consumption
.alpha (n,m) Bypass ratio
.mDotOverA2 (n,m) Mass flow per unit area at the diffuser exit
.forceOverA2 (n,m) Force per unit area at the diffuser exit
.rhoU (n,m) External airflow per unit area
d (1,1) Input data structure
p (1,1) Performance parameters
def (1,1) Definition data structure
.p p parameters
.d d parameters
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ACPro: ACEngine/JetEngineDefinitions ACPro: ACEngine/MachFromPR ACPro: ACEngine/MassFlow ACPro: ACEngine/MassFlowParameterR ACPro: ACEngine/PlotGasTurbineData ACPro: ACEngine/RFromCPAndGamma ACPro: ACEngine/RamRecovery ACPro: ACEngine/TempRatioFromMachAndGamma AerospaceUtils: AtmosphericCalculations/AtmGamma Common: Atmosphere/StdAtm Common: General/DeleteCell
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