A rocket nozzle produces 1 MN of thrust at sea level (ambient pressure and temperature 100 kPa and 300 K). The stagnation pressure and temperature are 5 MPa and 2800 K. Determine (a) the exit to throat area ratio, (b) exit Mach number, (c) exit velocity, (d) mass flow rate, and (e) exit area. Determine the thrust developed by the nozzle at an altitude of 20 km, where the ambient pressure and temperature are 5.46 kPa and 217 K. Assume the working fluid to be air with γ = 1.4.