Path: ACPro/ACEngine
% Compute Mach number and pressure for aerodynamics shocks.
The default for theta is 90 degrees, a normal shock.
Type AerodynamicShock for a demo.
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Form:
[m1, pTR, p1] = AerodynamicShock( m0, p0, gamma, theta )
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Inputs
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m0 (1,:) Free stream mach number
p0 (1,:) Free stream pressure
gamma (1,1) Fluid ratio of specific heats
theta (1,1) Oblique shock angle (rad)
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Outputs
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m1 (1,:) Mach number after the shock
pTR (1,1) pt1/pt0
p1 (1,:) Pressure after the shock
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Reference: Ames Research Staff, "Equations, Tables and Charts for
Compressible Flow," Report 1135.
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ACPro: ACEngine/MachAcrossShock ACPro: ACEngine/StreamlineShockAngle AerospaceUtils: AeroData/AtmData Common: Atmosphere/StdAtm Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/DispWithTitle Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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