|
SUPPORT SITE |
|
|
|
SUPPORT SITE |
|
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.
--------------------------------------------------------------------------
Form:
[m1, pTR, p1] = AerodynamicShock( m0, p0, gamma, theta )
--------------------------------------------------------------------------
------
Inputs
------
m0 (1,:) Free stream mach number
p0 (1,1) Free stream pressure
gamma (1,1) Fluid ratio of specific heats
theta (1,1) Oblique shock angle (rad)
-------
Outputs
-------
m1 (1,:) Mach number after the shock
pTR (1,1) pt1/pt0
p1 (1,:) Pressure after the shock
--------------------------------------------------------------------------
Reference: Ames Research Staff, "Equations, Tables and Charts for
Compressible Flow," Report 1135.
--------------------------------------------------------------------------
ACPro: ACEngine/MachAcrossShock Common: Atmosphere/StdAtm Common: Graphics/Plot2D
Back to the ACPro Module page