Engineering, 16.03.2020 18:44 nessuhbae6722
A convergent–divergent nozzle is designed to expand air from a chamber in which the pressure is 800 kPa and the temperature is 40°C to give Mach 2.5. The throat area of the nozzle is 0.0025 m2. Find a. The flow rate through the nozzle under design conditions b. The exit area of the nozzle c. The design back-pressure and the temperature of the air leaving the nozzle with this back-pressure d. The lowest back-pressure for which there is only subsonic flow in the nozzle e. The back-pressure at which there is a normal shock wave on the exit plane of the nozzle f. The back-pressure below which there are no shock waves in the nozzle g. The range of back-pressures over which there are oblique shock waves in the exhaust from the nozzle h. The range of back-pressures over which there are expansion waves in the exhaust from the nozzle i. The back-pressure at which a normal shock wave occurs in the divergent section of the nozzle at a point where the nozzle area is half way between the throat and the exit plane areas
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A convergent–divergent nozzle is designed to expand air from a chamber in which the pressure is 800...
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