A small rocket motor, fueled with hydrogen and oxygen, is tested on a thrust stand at a simulated altitude of 10 km. The motor is operated at chamber stagnation conditions of 1500 K and 8.0 MPa gage. The combustion product is water vapor, which may be treated as an ideal gas. Expansion occurs through a converging-diverging nozzle with design Mach number of 3.5 and exit area of 700 mm2. Evaluate the pressure at the nozzle exit plane. Calculate the mass How rate of exhaust gas. Determine the force exerted by the rocket motor on the thrust stand.
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