Air expands from a storage tank through a converging-diverging nozzle. (See Figure P4.4.) Under certain conditions, it is found that a normal shock exists in the diverging section of the nozzle at an area equal to twice the throat area, with the exit area of the nozzle equal to four times the throat area. Assuming isentropic flow except for the shockwaves, that the air behaves as a perfect gas with constant y = 1.4, and that the storage tank pressure and tem- perature are 200 kPa and 300 K, respectively, determine the following: a) A* for flow from inlet to shock, b) A for flow from shock to exit, c) the mach number at the nozzle exit plane, (d) the stagnation pressure at the nozzle exit plane, e) the exit plane static pressure, and f) the exit plane velocity. T,= 300 K %3D Po= 200 kPa Athroat = 50 cm? Aexit = 4 Atbroạt Akech = 2 Aren

Air expands from a storage tank through a converging-diverging nozzle. (See Figure P4.4.) Under certain conditions, it is found that a normal shock exists in the diverging section of the nozzle at an area equal to twice the throat area, with the exit area of the nozzle equal to four times the throat area. Assuming isentropic flow except for the shockwaves, that the air behaves as a perfect gas with constant y = 1.4, and that the storage tank pressure and tem- perature are 200 kPa and 300 K, respectively, determine the following: a) A* for flow from inlet to shock, b) A for flow from shock to exit, c) the mach number at the nozzle exit plane, (d) the stagnation pressure at the nozzle exit plane, e) the exit plane static pressure, and f) the exit plane velocity. T,= 300 K %3D Po= 200 kPa Athroat = 50 cm? Aexit = 4 Atbroạt Akech = 2 Aren

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

ChapterMA: Math Assessment

Section: Chapter Questions

Problem 1.1MA

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