1. An air flow at 90 psia, 1100 R, M =0.3 flows into a convergent-divergent nozzle with M = 1 at the throat. Assume a reversible flow with an exit area twice the throat area and find the exit pressure and temperature for subsonic exit flow to exist.
2. Air is expanded in a nozzle from 300 lbf/in.2, 1100 R, to 30 lbf/in.2. The mass flow rate through the nozzle is 10 lbm/s. Assume the flow is reversible and adiabatic and determine the throat and exit areas for the nozzle.