In: Physics
Sample practice Ch. 6B – Silimar to Homework 6-15
Consider a horizontal supersonic flow a Mach 2.8 with a static pressure and temperature of one atm and 20 C, respectively. This flow passes over a compression corner with the deflection angle of 16 degrees. The oblique shock generated at the corner propagates into the flow, and is incident on horizontal wall as shown in the figure. Calculate the angle made by the reflective shock wave with respect to the wall and the Mach number M3, pressure P3 and temperature T3 behind the reflected shock.
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