A supersonic stream at \(M_{1}=3.6\) flows past a compression corner with a deflection angle of \(20^{\circ}\). 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.

Figure 4.18:

Transcribed Image Text:

M Streamline Incident shock Mz B Reflected shock