A turbojet engine has a converging nozzle with variable area. At one sea level operating condition, the engine exhaust flow is 100 kg/s and the stagnation state entering the nozzle is 1100K and 3 atm. The specific heat ratio may be assumed constant at 1.33. If the nozzle is isentropic, find the required exit area. If instead the nozzle efficiency is 90%, find the exit stagnation pressure and the percentage increase in required exit area.