Path: ACPro/ACEngine
% Mass inflow for a supersonic diffuser -------------------------------------------------------------------------- Form: mA = MassInflowSupersonic( gamma, machNo2, piD, p0, t0, tauR ) -------------------------------------------------------------------------- ------ Inputs ------ gamma (1,1) Ratio of specific heats machNo2 (1,1) Mach number at station 2 piD (1,1) Diffuser pressure ratio (nearly 1) altitude (1,1) Altitude (m) cP (1,1) Specific heat constant pressure machNo (1,:) Mach number units (1,:) 'eng' or 'mks' ------- Outputs ------- mA (1,:) mdot/a --------------------------------------------------------------------------
ACPro: ACEngine/AOverAStar ACPro: ACEngine/MassFlowParameter AerospaceUtils: AeroData/AtmData 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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