Part II Calculations 6. A 20.5 half-angle wedge is mounted at 0'angle of attack in the test section of a supersonic wind tunnel. When the tunnel is operating, the wave angle from the wedge leading edge is measured to be 40'. What is the exit-to-throat area ratio of the tunnel nozzle? (15 marks) 7. Consider an infinitely thin flat plate at an angle of attack a=5 in a Mach 2.0 flow. Calculate the lift and wave-drag coefficient (a) Using oblique and expansion wave theory. (b) Using linearized theory (c) And compare the linearization error on lift and drag coefficients. (15 marks) 8. Consider a supersonic flow Ma-2.4, p=1.0x10' Pa, and T-273K. This flow is over a compression and expansion corner as shown in the figure. The deflection angle 0=15. Calculate M. P, T, AS, Po To and velocity behind the second corner. (15 marks) Ma = 2.4 first corner second corner Part III Applications Figure 2 Supersonic Flow over double corners 9. A diamond thin airfoil with wedge angle 0-10 as shown in the figure, draw the expansion and shock wave systems at Mach number 3 for angles of attack 0, 5'and 8", respectively (10 marks) 0 Figure 3A diamond thin airfoil