Problem 2 (20 pts) In this problem we are going to perform a simplified analysis of the NASA X-43 hypersonic aircraft shown in Figure 1, using compressible flow analysis. During its record flight, the vehicle flew at an altitude of 29 km (freestream temperature and pressure of 226 K and 14 kPa, respectively) at Mach 9.6 and angle of attack = 13. A shock wave emanated from the nose leading edge and created an extra compression lift on the vehicle windward side as the vehicle was scramjet powered through the atmosphere. Consider the simplified 2D schematic for the X-43 geometry shown in Figure 2, with 0 LE = 10, Lwind = 2 m, and Llee 1.8 Lwind. Assuming a calorically perfect air gas with 1.4, find the Mach number and the static pressure on all three surface of the vehicle and compute the lift-to-drag ratio. = = Ma EA-X Figure 1. The NASA X-43 scramjet powered hypersonic aircraft. Llee Leeward side OLE Windward side Lwind Figure 2. Schematic of simplified 2D hypersonic shape. Base Lbase