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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.

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.

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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Please only answer STEP 2 question. THIS IS MY 3RD TIME POSTING THE SAME QUESTION AND NOT GETTING THE ANSWER I NEED. DONT SOLVE FOR THE MAIN QUESTION, I NEED THE ANSWER TO THE SECOND PART OF THE QUESTION. 

If this tank/converging-diverging nozzle combination was to be used as a rocket's propulsion unit, would it produce more or less thrust as it flew higher and higher in altitude?
Transcribed Image Text:If this tank/converging-diverging nozzle combination was to be used as a rocket's propulsion unit, would it produce more or less thrust as it flew higher and higher in altitude?
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 Po= 200 kPa Athroat = 50 cm? Aexit = 4 Athroạt Ashock = 2 Athroat
Transcribed Image Text: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 Po= 200 kPa Athroat = 50 cm? Aexit = 4 Athroạt Ashock = 2 Athroat
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