Consider a horizontal supersonic flow at Mach 2.8 with a static pressure and temperature of \(1 \mathrm{~atm}\) and \(519^{\circ} \mathrm{R}\), respectively. This flow passes over a compression corner with a deflection angle of \(16^{\circ}\). The oblique shock generated at the corner propagates into the flow, and is incident on a horizontal wall, as shown in Fig. 4.18. Calculate the angle \(\Phi\) made by the reflected shock wave with respect to the wall, and the Mach number, pressure, and temperature behind the reflected shock.

Figure 4.18:

Transcribed Image Text:

M Streamline Incident shock to Reflected shock