EngineTable:

Path: ACPro/Airbreathing

% Generate an engine table for a matrix of altitudes and mach. 

   Each row of output is an altitude and each column a Mach number. 
--------------------------------------------------------------------------
   Form:
   [t, sFC] = EngineTable( type, h, m, d, p )
--------------------------------------------------------------------------

   ------
   Inputs
   ------
   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) 

   -------
   Outputs
   -------
   t           (:,:)  Thrust (N)
   sFC         (:,:)  Thrust specific fuel consumption

--------------------------------------------------------------------------
   See also MixedFlowTurbofan, RamjetH2
--------------------------------------------------------------------------

Children:

ACPro: ACEngine/MachFromMassFlowParameter
ACPro: ACEngine/MachFromPR
ACPro: ACEngine/MassFlowParameterR
ACPro: ACEngine/RamRecovery
ACPro: ACEngine/TempRatioFromMachAndGamma
ACPro: Airbreathing/EngineExample
ACPro: Airbreathing/MixedFlowTurbofan
ACPro: Airbreathing/Ramjet
AerospaceUtils: AeroData/AtmData
AerospaceUtils: AtmosphericCalculations/AtmGamma
Common: Atmosphere/RFromCPAndGamma
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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