The hot gas supply to a propulsion nozzle is at a pressure of 55 kPa and a temperature of 800 K. The ambient pressure is 15 kPa. If the ratio of specific heats is 1.33, approximately constant, and the molecular weight of the mixture is 30, determine the ratio of gross thrusts (contribution to engine thrust made by the exhaust nozzle only) for: a. The nozzle is converging-diverging with the area ratio for correct expansion to ambient pressure.