A C-D nozzle is to be designed to produce a flight Mach number of 3.0 for...

A C-D nozzle is to be designed to produce a flight Mach number of 3.0 for the atmospheric conditions (pressure and temperature) at 15 km altitude in the test section of a supersonic wind tunnel. The diameter of the test section is 10 cm. Assume the gas has Y(gamma) = 1.4 and R = 2.077 kJ/kg*K, determine (a) the mass flow rate that must be provided, (b) the nozzle throat area, (c) the reservoir temperature and (d) the reservoir pressure.

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samet mamat answered 1 year ago

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