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Final Problem 1 (13 pts) Consider a rocket designed with a nozzle with an area ratio of 1000. The throat diameter is 125 mm. The combustion temperature and pressure are 2500 K and 150 atm in the reservoir of the rocket. The combustion products may be modeled as a perfect gas with a ratio of specific heats of 1.25 and a molecular weight of 35 g/mol. At a standard altitude of 25 km the temperature, density and pressure are 217 K, 4e- 2 kg/m3, and 2.5 kPa, respectively. Find: a) The gas constant (the universal gas constant is 8.314 J/mol K) and exit area and exit diameter b) The Mach number, pressure, temperature, and velocity at the nozzle exit c) The mass flow rate, effective exhaust velocity, thrust force, and specific impulse at 25 km