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Q2) Air expand from storage tank through a figure. Under certain condition it is found that a normal shock wave 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 fourth times the throat area. Assuming isentropic flow except for shock waves, that the air behaves as a perfect gas with constant (-1.4), and that the storage tank pressure and temperature are 200kpa, and 300K,

Q2) Air expand from storage tank through a figure. Under certain condition it is found that a normal shock wave 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 fourth times the throat area. Assuming isentropic flow except for shock waves, that the air behaves as a perfect gas with constant (-1.4), and that the storage tank pressure and temperature are 200kpa, and 300K,

Elements Of Electromagnetics
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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Q2) Air expand from storage tank through a convergent-divergent nozzle as in figure. Under certain condition it is found that a normal shock wave 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 fourth times the throat area. Assuming isentropic flow except for shock waves, that the air behaves as a perfect gas with constant (y-1.4), and that the storage tank pressure and temperature are 200kpa, and 300K, determine the following. a) Critical area for flow from inlet to shock. b) Critical area for flow from shock to exit. c) Mach number at nozzle exit plane. d) Stagnation pressure at nozzle exit plane. e) Exit plane static pressure. f) Exit plane velocity. T. = 300 K Po = 200 kPa Athroat = 50 cm² Aexit = 4 Ahroat Ashock = 2 Athroor
Transcribed Image Text:Q2) Air expand from storage tank through a convergent-divergent nozzle as in figure. Under certain condition it is found that a normal shock wave 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 fourth times the throat area. Assuming isentropic flow except for shock waves, that the air behaves as a perfect gas with constant (y-1.4), and that the storage tank pressure and temperature are 200kpa, and 300K, determine the following. a) Critical area for flow from inlet to shock. b) Critical area for flow from shock to exit. c) Mach number at nozzle exit plane. d) Stagnation pressure at nozzle exit plane. e) Exit plane static pressure. f) Exit plane velocity. T. = 300 K Po = 200 kPa Athroat = 50 cm² Aexit = 4 Ahroat Ashock = 2 Athroor
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