AerodynamicShock:

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,:)  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

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   Reference: Ames Research Staff, "Equations, Tables and Charts for
              Compressible Flow," Report 1135.
--------------------------------------------------------------------------

Children:

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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