1. Shock-expansion theory Consider a thin airfoil with an isosceles section as shown in Fig. 1 where the base AB is taken to be the chord of length c and is at the bottom. The acute angles at A and B are 6. The airfoil is at an incidence of a = 4 facing an incoming flow at M = 3. a. [10 pts] Determine the pressure ratios p2/P1, P3/P and p4/p. Show your steps including usage of the Compressible Aerodynamics Calculator. b. [10 pts] Determine the angle of the slipline relative to the incoming flow direction. Also, determine the Mach numbers M5 and M6. M = 3 0 = 6 B a=4 Figure 1.1. Schematic for Problem 1 (figure not to scale).