a) Consider an isentropic compressible flow in a supersonic nozzle. Describe how the Mach number, the static pressure, s

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a) Consider an isentropic compressible flow in a supersonic nozzle. Describe how the Mach number, the static pressure, s

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A Consider An Isentropic Compressible Flow In A Supersonic Nozzle Describe How The Mach Number The Static Pressure S 1
A Consider An Isentropic Compressible Flow In A Supersonic Nozzle Describe How The Mach Number The Static Pressure S 1 (149.32 KiB) Viewed 24 times
a) Consider an isentropic compressible flow in a supersonic nozzle. Describe how the Mach number, the static pressure, static temperature, density and total pressure change in the diverging section. (5 marks) b) Air flows isentropically through a converging nozzle to a receiver pipe as shown in Figure Q1 below. The cross-sectional area of the throat of the converging nozzle is 0.02 m². The stagnation pressure and stagnation temperature of the air are 101 kPa and 287 K, respectively. i) Calculate the pressure in the receiver for a choke flow to take place in the nozzle. Determine the mass flow rate through the nozzle if the receiver pressure is 70 kPa. [Use air properties of k = 1.4, R = 287 J/kgK] ii) Converging nozzle flow Receiver pipe Figure Q1 D (7 marks)
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