Engineering, 10.04.2020 16:51 awarnk

A rocket nozzle is designed to operate isentropically at 20 km with a chamber with stagnation pressure of 2.0 MPa and temperature of 3000 K. If the products of combustion are assumed to behave as a perfect gas with constant specific heats (y = 1.3 and MW = 20 kg/kmol), determine the design thrust for a nozzle throat area of 0.25 m². Hint: Thrust, T = m Volk + Por.

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A rocket nozzle is designed to operate isentropically at 20 km with a chamber with stagnation pressu...