A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with a velocity of 2000 m/s, and a density of 1.0 kg/m in the test section. Find the temperature and pressure in the test section and the upstream stagnation conditions. The fluid is helium.
A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with a velocity of 2000 m/s, and a density of 1.0 kg/m in the test section. Find the temperature and pressure in the test section and the upstream stagnation conditions. The fluid is helium.
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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A nozzle for a supersonic wind tunnel is designed to achieve a Mach number of 3.0, with a velocity of 2000 m/s, and a
3
density of 1.0 kg/m in the test section. Find the temperature and pressure in the test section and the upstream
stagnation conditions. The fluid is helium.
Te = i 217
Pe=
To = i
12.1
868.325
PO = i 387.2
K
kPa
K
kPa
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