1. A supersonic passenger plane is cruising at an altitude of 60,000 ft. A normal shock forms in front of the nose of the plane. A pitot-static system on the

nose (behind the shock) measures the pressure ratio between stagnation pressure and static pressure to be 1.2256. a. Calculate the cruise Mach number of the aircraft (10 points). b. The airfoil selected for the aircraft has a critical Mach number of 0.65. The airplane is designed to have a variable-sweep wing to improve efficiency between M = 0.75 and its cruise Mach number. Calculate the required range of wing sweep angles in degrees for minimum transonic drag and wave drag (in supersonic condition if applicable). (12 points)