QUESTION 5At the inlet to an axial diffuser the velocity of the approaching air is 420 m/s, the stagnationpressure 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) thestatic temperature, static pressure, and Mach number at inlet and the diffuser efficiency; (ii) theMach number at exit and entry. For air take y 1.376 and R 287 J/ (kg K)

Answered: QUESTION 5 At the inlet to an axial…

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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D5. A converging-diverging nozzle operates with air and subsonic flow at the inlet and supersonic flow at the outlet with no shacks inside the nozzle. Determine the mach number and static pressure at the outlet if the area of the outlet is 0.900 m2, the area of the throat is 0.490m2, and the stagnation pressure is 215 kPa.
The discharge air from a convergent-divergent nozzle at a Mach number of 1.72. The exit pressure is 15 psia, and the temperature is 155 degree F. For isentropic expansion and a negligible inlet velocity, calculate the stagnation pressure, psia.A. 72.31 B. 74.31 C. 76.31 D. 78.31
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