In an afterburning jet engine during static test, the fluid enters the afterburner at a stagnation temperature of 900 K and stagnation 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, which has an inlet Mach number of 0.3. Without afterburning, the stagnation pressure loss between afterburner entrance and exit is 3%. When the afterburner is operating, the exit stagnation temperature rises to 1800 K. The afterburning process is to be modeled as constant-area heat addition. In both cases the nozzles flow is simply converging and you may assume air (y = 1.4). Determine the required nozzle exit flow area in both cases.