In Example 4.1, the free-stream Mach number is increased to 5. Calculate the pressure and Mach number behind the wave, and compare these results with those of Example 4.1.

Data From Example 4.1:

A uniform supersonic stream with \(M_{1}=3.0, p_{1}=1 \mathrm{~atm}\), and \(T_{1}=288 \mathrm{~K}\) encounters a compression corner (see Fig. 4.4a) which deflects the stream by an angle \(\theta=20^{\circ}\). Calculate the shock wave angle, and \(p_{2}, T_{2}, M_{2}, p_{o_{2}}\), and \(T_{o_{2}}\) behind the shock wave.

Transcribed Image Text:

M > 1 1 (a) Concave corner Supersonic flow over a corner. Oblique shock T>T (2) M