Consider the geometry shown in Fig. 4.19. Here a supersonic flow with Mach number, pressure, and temperature \(M_{1}, p_{1}\), and \(T_{1}\), respectively, is deflected through an angle \(\theta_{1}\) by a compression corner at point \(A\) on the lower wall, creating an oblique shock wave emanating from point \(A\). This shock impinges on the upper wall at point \(B\). Also precisely at point \(B\), the upper wall is bent downward through the angle \(\theta_{2}\). The incident shock is reflected at point \(B\), creating a reflected shock which propagates downward and to the right in Fig. 4.19. Consider a flow where \(M_{1}=3, p_{1}=1 \mathrm{~atm}\), and \(T_{1}=300 \mathrm{~K}\). Consider the geometry as sketched in Fig. 4.19 where \(\theta_{1}=14^{\circ}\) and \(\theta_{2}=10^{\circ}\). Calculate the Mach number, pressure, and temperature in region 3 behind the reflected shock wave.

Figure 4.19:

Transcribed Image Text:

M P1 T A Incident shock B 0+02 Reflected shock