Engineering, 13.12.2019 02:31 katerin4738

At rated thrust, a liquid-fueled rocket motor consumes 80 kg/s of nitric acid as oxidizer and 32 kg/s of aniline as fuel. flow leaves axially at 180 m/s relative to the nozzle and at 110 kpa. the nozzle exit diameter is d = 0.6 m. calculate magnitude of the thrust produced by the motor on a test stand at standard sea-level pressure.

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At rated thrust, a liquid-fueled rocket motor consumes 80 kg/s of nitric acid as oxidizer and 32 kg/...

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