Question: Uniform flow ( air ) at M = 2 . 0 with T = 3 0 0 K and P = 1 0 1 3

Uniform flow (air) at M =2.0 with T =300 K and P =101325 Pa passes over a wedge of 10o halfangle. Determine the Mach number, static and stagnation pressure, and static temperature just
downstream of the shock.

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