A wind tunnel nozzle is designed to yield a parallel uniform flow of air with a Mach number of 3.0. The stagnation pressure of the air supply reservoir is 7000 kPa, and the nozzle exhausts into the atmosphere (100 kPa). Calculate the flow angle at the exit lip of the nozzle. Ma-3.0 100 kPa 7000 kPa angle = ?

A wind tunnel nozzle is designed to yield a parallel uniform flow of air with a Mach number of 3.0. The stagnation pressure of the air supply reservoir is 7000 kPa, and the nozzle exhausts into the atmosphere (100 kPa). Calculate the flow angle at the exit lip of the nozzle. Ma-3.0 100 kPa 7000 kPa angle = ?

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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Question

A wind tunnel nozzle is designed to yield a parallel uniform flow of air with a Mach number of 3.0. The
stagnation pressure of the air supply reservoir is 7000 kPa, and the nozzle exhausts into the atmosphere
(100 kPa). Calculate the flow angle at the exit lip of the nozzle.
Ma-3.0
100 kPa
7000 kPa
angle = ?

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