In an afterburning jet engine during a static test, the fluid entering the after- burner has a temperature of 900 K, a pressure of 0.235 MPa and a mass flow rate of 75 kg/s. These conditions are maintained with and without operation of the afterburner. Without afterburning, the stagnation pressure loss be- tween afterburner entrance and exit is 3 percent and the specific heat ratio of the fluid in the nozzle is 1.33. When the afterburner is operating, the exit stagnation temperature rises to 1800 K, the stagnation pressure loss changes to 8 percent and the specific heat ratio in the nozzle drops to 1.29. In both cases the nozzle flow is simply converging and choked. Determine the re- quired nozzle exit area in both cases.