Q2) Air expand from storage tank through a convergent-divergent nozzle as infigure. Under certain condition it is found that a normal shock wave exists in thediverging section of the nozzle at an area equal to twice the throat area, with theexit area of the nozzle equal to fourth times the throat area. Assuming isentropicflow 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 KPo = 200 kPaAthroat = 50 cm²Aexit=4 AhroatAshock = 2 Athroor

Given storage tank pressure and temperature are 200kPa and 300 K we have to find (I) a critical…

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

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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