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). The figures below depict 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. The first was computed on a structured grid, the second on an unstructured.

Pictures of surface grids in the same hexahedral and tetrahedral families are available also. Note that the grids in the two families are closed slightly differently at the wingtip.

Different graphics packages were used to prepare the images, so although the contouring styles are intentionally similar, they do not match perfectly in the hue or bin patterns in the color spectra.

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.]

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

[Note: This flow simulation used a 3D unstructured grid of 357,900 vertices on 80 processors of a Cray T3E.]

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