b. Air flows in a converging-diverging nozzlefrom stagnation conditions at P, = 500 kPaand T. = 400 K as shown in Fig.2. The exitThroatTostatic pressure is 450 kPa, and the throatMEPoand exit areas are 0.01 m? and 0.015 m2Porespectively. Assuming isentropic flow,SupersonienozzleAgdetermine the Mach number, ME at exitand the mass flow rate th when the flow issupersonic in the divergence section of thePE(Ma, = 1)duct.(Take for air, K=1.4, and R= 287 m?/s?.K)Fiq.2

Given:- P0 = 500 kPaT0 = 400 kAt = 0.01 m2Ae = 0.015 m2k = 1.4R = 287 m2/s2k

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

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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