A converging-diverging nozzle has a design Mach number of 2.0 . The stagnation pressure at the nozzle inlet is 100 psia. The nozzle exhausts to a back pressure of 5 psia. Sketch the flow field downstream of the nozzle exit and determine: (a) The exit pressure of the nozzle (b) The Mach number, flow direction, and pressure immediately outside the nozzle.