PROBLEMS1. Consider a scenario in which supersonic flow iscompressed and turned by 18° through an oblique shock.Consider the gas to be calorically perfect Air withupstream properties as follows: M, = 7, P, = 7.5 kPa, T1 =225 K. Find the following:MI6=180(a) shock wave angle, ß. (you can either use the analytical solution from the notes ornumerically find the root, whichever method you prefer).(b) downstream Mach number, M3.(c) downstream static pressure, P3.(d) downstream static temperature, T3.(e) total pressure ratio, Po.3 / Po,1-(f) entropy change, (s3-S).(g) use the VT Oblique Shock Calculator Applet to verify your results for this problem.

Given: M1=7 P1=7.5 KPa T1=225 K For air Shock angle, from chart between shock angle, Mack number…

Answered: PROBLEMS 1. Consider a scenario in…

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