Consider the supersonic flow of air over a two-dimensional wedge with a half angle of 10 degrees at 70 kPa, 260 kelvin, and mach number 2.4 after shock. If the axis of the wedge is tilted 25 degrees beforehand, determine the post-shock Mach number, temperature and pressure on the wedge.

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A: Note: As per Bartleby guidelines only 3 subparts have to be solved at a time. So upload other parts…