Design an attitude control nozzle for a spacecraft

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Reference no: EM131346982

1. Design a converging-diverging nozzle system that can be used to demonstrate supersonic flow in the classroom. Choose a convenient gas, inlet conditions, and exit Mach number. Determine the necessary area ratios, pressures, and temperatures throughout the system.

2. Design an attitude control nozzle for a spacecraft that produces 50.0 N of thrust using compressed helium gas stored at 50.0 MPa and 0.00°C. Assume the nozzle discharges into a total vacuum. Specify the nozzle inlet, throat, and exit areas as well as the exit Mach number.

Reference no: EM131346982

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