Multi-Model Multi-Domain Computational Methods: Shocks

The characteristic lambda-shock for compressible Euler flow is shown below in a surface plot of Mach number (the local tangential velocity magnitude divided by the local sound speed). This figure depicts flow over an ONERA M6 wing for the transonic case of freestream Mach number of 0.84 and an angle of attack of 3.06 degrees.

Mach number contours of the converged flowfield on the upper wing surface.

[Note: This flow simulation used a 3D structured grid of size 194x34x34 on 16 processors of an IBM SP2. This figure shows only selected grid lines for the z=1 logical plane due to resolution constraints for visualization.]

A picture of just the grid is available also.

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