A supersonic wind tunnel is in the design stage. It is to be driven by a large upstream reservoir of compressed air and discharges to atmospheric conditions downstream. The test section has a constant cross-sectional area and lies downstream of a throat, which is a converging-diverging section that serves to accelerate the flow to supersonic conditions. For the duration of any given experiment, the reservoir can be considered to have constant stagnation conditions that are To = 313K and po = 6x105 Pa. The specific gas constant R = 287 J kg-1 K1 and the specific heat ratio is y = 1.4. The wind tunnel test section is designed to run with cross-sectional area A (test section ) = 1.2 m² and Mach number M (test section ) = 3.5. Find the area of the throat that lies between the reservoir and the test section. Give your answer in m² to two decimal places.
A supersonic wind tunnel is in the design stage. It is to be driven by a large upstream reservoir of compressed air and discharges to atmospheric conditions downstream. The test section has a constant cross-sectional area and lies downstream of a throat, which is a converging-diverging section that serves to accelerate the flow to supersonic conditions. For the duration of any given experiment, the reservoir can be considered to have constant stagnation conditions that are To = 313K and po = 6x105 Pa. The specific gas constant R = 287 J kg-1 K1 and the specific heat ratio is y = 1.4. The wind tunnel test section is designed to run with cross-sectional area A (test section ) = 1.2 m² and Mach number M (test section ) = 3.5. Find the area of the throat that lies between the reservoir and the test section. Give your answer in m² to two decimal places.
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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Transcribed Image Text:A supersonic wind tunnel is in the design stage. It is to be driven by a large upstream reservoir of compressed air and discharges to atmospheric conditions downstream. The
test section has a constant cross-sectional area and lies downstream of a throat, which is a converging-diverging section that serves to accelerate the flow to supersonic
conditions. For the duration of any given experiment, the reservoir can be considered to have constant stagnation conditions that are To = 313K and po = 6x105 Pa. The specific
gas constant R = 287 J kg-¹ K-1 and the specific heat ratio is y = 1.4.
The wind tunnel test section is designed to run with a cross-sectional area A (test section ) = 1.2 m² and Mach number M (test section ) = 3.5.
Find the area of the throat that lies between the reservoir and the test section. Give your answer in m² to two decimal places.
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A supersonic wind tunnel is in the design stage. It is to be driven by a large upstream reservoir of compressed air and discharges to atmospheric conditions downstream. The test section has a constant cross-sectional area and lies downstream of a throat, which is a converging-diverging section that serves to accelerate the flow to supersonic conditions. For the duration of any given experiment, the reservoir can be considered to have constant stagnation conditions that are To = 313K and po = 6x105 Pa. The specific gas constant R = 287 J kg-¹ K-1 and the specific heat ratio is y = 1.4. The wind tunnel test section is designed to run with a cross-sectional area A (test section ) = 1.2 m² and Mach number M (test section ) = 4. Find the area of the throat that lies between the reservoir and the test section. Give your answer in m² to two decimal places.
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