In: Mechanical Engineering
A uniform supersonic airflow traveling at passes over a wedge (as Figure). An oblique shock, making an angle of 40° with the flow direction, is attached to the wedge under these flow conditions. If the static pressure and temperature in the uniform flow are 20k Pa, -10 °C, respectively. Determine the static pressure and temperature behind the wave, the Mach number of the flow passing over the wedge, and the wedge half-angle.