Design a converging-diverging nozzle for a spacecraft, Ask an Expert

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Design a converging-diverging nozzle for a spacecraft thruster that has an exit Mach number of 5.00 when using compressed helium at 50.0 MPa, and 0.00°C. Assume the nozzle exhausts into a total vacuum.

Plot the nozzle diameter vs. length along the nozzle, keeping the angle of the diverging wall to less than 10o with the horizontal to prevent flow separation.

Show the positions along the nozzle where M = 1, 2, 3, 4, and 5. Determine the mass flow rate through your nozzle.

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Reference No.:- M92100545

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