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Panel - Compressible Flow Over an Airfoil
Panel - Compressible Flow Over an Airfoil

Exercise - Mesh Refinement

Looking more closely at the Stanford results, we can see that they captured a shock wave along the upper section of the wing, as indicated by the tight clustering of contour lines in-between the blue and green bands.  We need to refine the AIM mesh to capture that same effect in as much detail.

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