At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation pressure is 300 kPa, and the stagnation temperature is 600 K. At exit the stagnation pressure is 285 kPa and the static pressure 270 kPa. Using compressible flow analysis, determine(i) the static temperature, static pressure, and Mach number at inlet and the diffuser efficiency;(ii) the Mach numbers at exit and entry.For air take γ ¼ 1.376 and R ¼ 287 J/(kg K). 11.At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation pres-sure is 300 kPa, and the stagnation temperature is 600 K. At exit the stagnation pressure is285 kPa and the static pressure 270 kPa. Using compressible flow analysis, determine(i) the static temperature, static pressure, and Mach number at inlet and the diffuser efficiency;(ii) the Mach numbers at exit and entry.For air take y = 1.376 and R = 287 J/(kg K).

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Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation pressure is 300 kPa, and the stagnation temperature is 600 K. At exit the stagnation pressure is 285 kPa and the static pressure 270 kPa. Using compressible flow analysis, determine
(i) the static temperature, static pressure, and Mach number at inlet and the diffuser efficiency;
(ii) the Mach numbers at exit and entry.
For air take γ ¼ 1.376 and R ¼ 287 J/(kg K).

11.
At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnation pres-
sure is 300 kPa, and the stagnation temperature is 600 K. At exit the stagnation pressure is
285 kPa and the static pressure 270 kPa. Using compressible flow analysis, determine
(i) the static temperature, static pressure, and Mach number at inlet and the diffuser efficiency;
(ii) the Mach numbers at exit and entry.
For air take y = 1.376 and R = 287 J/(kg K).

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