Engineering, 09.04.2020 00:16 mlguerrero12
A supersonic stream at M1 = 3.6 flows past a compression corner with a deflection angle of 20o. The incident shock wave is reflected from an opposite wall, which is parallel to the upstream supersonic flow, as sketched in Fig. 4.18. Calculate the angle of the reflected shock relative to the straight wall.
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A supersonic stream at M1 = 3.6 flows past a compression corner with a deflection angle of 20o. The...
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