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b. Air flows in a converging-diverging nozzle Throat from stagnation conditions at P, - 500 kPa To ME Po and T. = 400 K as shown in Fig.2. The exit static pressure is 450 kPa, and the throat and exit areas are 0.01 m? and 0.015 m? Supersonie nozzle Ag Po respectively. Assuming isentropic flow, determine the Mach number, ME at exit PE and the mass flow rate h when the flow is supersonic in the divergence section of the (Ma, = 1) duct. Fig.2 (Take for air, K=1.4, and R= 287 m?/s?.K)

b. Air flows in a converging-diverging nozzle Throat from stagnation conditions at P, - 500 kPa To ME Po and T. = 400 K as shown in Fig.2. The exit static pressure is 450 kPa, and the throat and exit areas are 0.01 m? and 0.015 m? Supersonie nozzle Ag Po respectively. Assuming isentropic flow, determine the Mach number, ME at exit PE and the mass flow rate h when the flow is supersonic in the divergence section of the (Ma, = 1) duct. Fig.2 (Take for air, K=1.4, and R= 287 m?/s?.K)

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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b. Air flows in a converging-diverging nozzle from stagnation conditions at P, = 500 kPa and T. = 400 K as shown in Fig.2. The exit Throat To static pressure is 450 kPa, and the throat ME Po and exit areas are 0.01 m? and 0.015 m2 Po respectively. Assuming isentropic flow, Supersonie nozzle Ag determine the Mach number, ME at exit and the mass flow rate th when the flow is supersonic in the divergence section of the PE (Ma, = 1) duct. (Take for air, K=1.4, and R= 287 m?/s?.K) Fiq.2
Transcribed Image Text:b. Air flows in a converging-diverging nozzle from stagnation conditions at P, = 500 kPa and T. = 400 K as shown in Fig.2. The exit Throat To static pressure is 450 kPa, and the throat ME Po and exit areas are 0.01 m? and 0.015 m2 Po respectively. Assuming isentropic flow, Supersonie nozzle Ag determine the Mach number, ME at exit and the mass flow rate th when the flow is supersonic in the divergence section of the PE (Ma, = 1) duct. (Take for air, K=1.4, and R= 287 m?/s?.K) Fiq.2
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