A supersonic nozzle produces a flow of nitrogen at M = 2.0 and p = 0.7 bar. This discharges into an ambient pressure of 1.0 bar, producing the flow pattern shown in Figure 8.8. (a) Compute the pressures, Mach numbers, and flow directions in regions 2, 3, and 4. (b) Make a sketch of the exit jet showing all angles to scale (streamlines, shock lines, and Mach lines). M = 1.6 = 8.5 psia P 12 chord 6 ft- = Figure P8.8 12