(20 points). Consider again the SR-71 Blackbird. As we discussed, crucial to the aircraft performance was the engine inlet spike assembly, which represented a conical structure located in the center of each inlet. Moving the spike back and forth controlled the air flow into the engine (this inlet spike is the focus of the Bonux Project 2). Assume typical flight conditions for SR-71, namely M = 3.3 and P = 0.028 atm. a. (4 points). Consider a simplified case with no inlet spike, where a normal shock stands ahead of the engine inlet as shown in the figure below. Using Matlab or some other program (not the textbook tables or NACA 1135) complete the table. Be sure to attach your program. M, P Region 1 2 1 normal shock M 3.3 2 P (static) 0.028 atm Po (stagnation) b. (12 points). Now consider a more realistic case, where the inlet spike diverts the flow and causes two oblique shocks to form. Using Matlab or some other program (not the textbook tables or the NACA 1135) complete the following table for the properties in each of the regions. Also assume that 0 = 15 and the spike is actually a 2D wedge. Be sure to attach your program. 1 M, P 2 0 = 15 3 Region Flow angle from horizontal 0 1 2 3 Angle of the shock to the left of the region with respect to the horizontal M 3.3 P (static) Po (stagnation) 0.028 atm c. (4 points). What can you say about the impact of the inlet in part (a) vs. part (b) in terms of the overall performance of the engine and its efficiency in generating thrust.