Air at a pressure and temperature of 30 kPa and –20°C flows at a Mach number of 3.5 down a wide duct. The upper wall of the duct turns sharply through an angle of 5° leading to the formation of an oblique shock wave as shown in the figure. Find the Mach number, temperature, and pressure behind the shock wave. As shown in the figure, this shock wave impinges the lower wall of the duct exactly at a point where the lower wall turns away from the flow through an angle of 2°. Find the Mach number, pressure, and temperature behind the “reflected” wave.