A small, solid fuel rocket motor is tested on a thrust stand. The chamber pressure and temperature are 4 MPa and 3250 K. The propulsion nozzle is designed to expand the exhaust gases isentropically to a pressure of 75 kPa. The nozzle exit diameter is 25 cm. Treat the gas as ideal with k 5 1:25 and R 5 300 J=___ Determine the mass flow rate of propellant gas and the thrust force exerted against the test stand.
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