Path: AC/Aero
% Computes impact to static pressure ratio from Mach number and gamma.
For supersonic flow uses the Rayleigh pitot tube formula.
--------------------------------------------------------------------------
Form:
pR = PressureRatioFromMach( gamma, m )
--------------------------------------------------------------------------
------
Inputs
------
gamma (1,:) Ratio of specific heats
m (1,:) Mach number
-------
Outputs
-------
pR (1,:) Pressure ratio
--------------------------------------------------------------------------
See also: RayleighPitotTube
--------------------------------------------------------------------------
Reference: Anderson, John D. Introduction to Flight, Third Edition,
McGraw-Hill, 1989. Ch. 4, Basic Aerodynamics
--------------------------------------------------------------------------
AC: Aero/RayleighPitotTube 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
Back to the AC Module page