A flat plate separates two supersonic air flows. The flow along the upper surface has a Mach number of 1.4 and a stagnation pressure of 55.3 psia. The flow along the lower surface has a Mach number of 3.5 and a stagnation pressure of 316psia. At the end of the plate, the flows come together and must adjust themselves. Calculate the flow field downstream of the plate, i.e. determine the Mach number, static pressure, and flow direction for each region behind the plate.