The products of combustion enter a nozzle of a jet engine at a total pressure of 18 lbf/in 2, and a total temperature of 1200 F. The atmospheric pressure is 6.75 lbf/in 2. The nozzle is convergent, and the mass flow rate is 50 lbm/s. Assume the flow is adiabatic. Determine the exit area of the nozzle.