1. Shock impingement at a corner a. A sharp wedge with a half-angle of 0 = 7 to a uniform, supersonic incoming air flow at M = 2.25 and a pressure of p = 50 kPa (absolute) as shown in the schematic, Fig. 1a. The attached shock from the tip of the wedge impinges a surface parallel to the incoming flow. The impinging shock is reflected off this surface. [10 pts] Determine M2, P2, and M3, P3. M = 2.25 P = 50 kPa 0 = 7 3 Figure 1a. Schematic for Problem la (figure not to scale). b. If at the point of impingement, the surface is inclined at a = 3 anticlockwise with respect to the incoming flow, as shown in Fig. 1b. [5 pts] Determine M3, P3 in this case. M = 2.25 0 = 7 P = 50 kPa a = 3 Figure 1b. Schematic for Problem 1b (figure not to scale). c. If at the point of impingement, the surface is inclined at a = 10 clockwise with respect to the incoming flow, as shown in Fig. 1c. This causes the flow in to expand. [5 pts] Determine M3, P3 in this case. M = 2.25 P = 50 kPa 0 = 7 a = 10 Figure 1c. Schematic for Problem 1c (figure not to scale).