PROBLEMS 1. Consider a scenario in which supersonic flow is compressed and turned by 180 through an oblique shock. Consider the gas to be calorically perfect Air with upstream properties as follows: M =7, P = 7.5 kPa, T = 225 K. Find the following: ML 6=180 (a) shock wave angle, ß (you can either use the analytical solution from the notes or numerically 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, Po3/ Po,1- (f) entropy change, (S3-S1). (g) use the VT Oblique Shock Calculator Applet to verify your results for this problem.

PROBLEMS 1. Consider a scenario in which supersonic flow is compressed and turned by 180 through an oblique shock. Consider the gas to be calorically perfect Air with upstream properties as follows: M =7, P = 7.5 kPa, T = 225 K. Find the following: ML 6=180 (a) shock wave angle, ß (you can either use the analytical solution from the notes or numerically 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, Po3/ Po,1- (f) entropy change, (S3-S1). (g) use the VT Oblique Shock Calculator Applet to verify your results for this problem.