Flat plate is oriented at angle of attack a 1 = 5? to the incoming supersonic stream, as shown in Figure 3.31. The upstream air pressure and temperature are p 1 = 101.3 kPa and T 1 = 288 K, and the...

Flat plate is oriented at angle of attack a 1 = 5? to the incoming supersonic stream, as shown in Figure 3.31. The upstream air pressure and temperature are p 1 = 101.3 kPa and T 1 = 288 K, and the Mach number is M 1 = 2.9. (a) Find the pressure above and below the plate. (b) Assuming that the flow after the plate is in the direction of the incoming stream, find the pressure after the plate for the air that flows over the plate and for that which flows under the plate. (Here it is assumed that no slip line forms).