Consider the purely subsonic flow of air in a convergent- divergent nozzle. the inlet, throat, and exit area are 1 m2, 0.7 m2, and 0.85 m2, respectively. if the inlet mach number is 0.30 and the inlet pressure is 0.8 × 105 pascals, calculate: (a) the static pressure p at the throat if the mach number at the throat is 0.46. (b) the static pressure p at the exit if the mach number at the exit is 0.36 figure 5: converging-diverging nozzle.