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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1. Find the pressure of air at a point in a stream where M equals 1.8 when the pressure and Mach number at another point in the stream are 25 psia and 0.8 respectively. Assume isentropic conditions. 2. Air having a reservoir pressure of 30 psia and density of 0.15 lb/ft is accelerated to a Mach number of 1.6. Find the static pressure, density, and temperature at this Mach number. 3. Consider the flow of air through a supersonic nozzle. The reservoir pressure and temperature are 5 atm and 500 K, respectively. If the Mach number at the nozzle exit is 3, calculate the exit pressure , temperature, and density. 4. A supersonic nozzle is a convergent-divergent duct , which is fed by a large reservoir at the inlet to the nozzle. In the reservoir of the nozzle, the pressure and temperature are 10atm and 550°R , respectively. At the nozzle exit, the pressure is 1 atm. Calculate the temperature and density of the flow at the exit. Assume the flow is isentropic and , of course, compressible. 5.…

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