Path: ACPro/ACEngine
% Computes the mass flow divided by the inlet area. The code is based on a constant Mach number at station 2 which is the exit of the diffuser and inlet to the fan or compressor. -------------------------------------------------------------------------- Form: mDot = MassFlow( m0, p0, t0, piDMax, eD, gamma, r, m2, units ) -------------------------------------------------------------------------- ------ Inputs ------ m0 (1,:) Inlet mach number p0 (1,1) Inlet pressure t0 (1,1) Inlet temperature piDMax (1,1) Maximum diffuser pressure ratio eD (1,1) Diffuser efficiency gamma (1,1) Rate of specific heats, cP/cV r (1,1) Gas constant m2 (1,1) Mach number at exit of diffuser units (1,:) 'eng' or 'mks' ------- Outputs ------- mDot (1,:) Mass flow --------------------------------------------------------------------------
ACPro: ACEngine/AOverAStar ACPro: ACEngine/MassFlowParameterR ACPro: ACEngine/RamRecovery AerospaceUtils: AeroData/AtmData AerospaceUtils: AtmosphericCalculations/AtmGamma 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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