Air discharges isentropically on a supersonic wind tunnel which is designed to achieve supersonic flow on the test section. It can be done by choking the air at the throat of a converging-diverging nozzle, wherein at the throat, the local speed is equal to the speed of sound. At the reservoir, the pressure and temperature are 500 kilopascals and 882 Kelvin, respectively. If the flow rate along the nozzle is constant at 170.1 kg/s, compute for the area at the throat.
Air discharges isentropically on a supersonic wind tunnel which is designed to achieve supersonic flow on the test section. It can be done by choking the air at the throat of a converging-diverging nozzle, wherein at the throat, the local speed is equal to the speed of sound. At the reservoir, the pressure and temperature are 500 kilopascals and 882 Kelvin, respectively. If the flow rate along the nozzle is constant at 170.1 kg/s, compute for the area at the throat.
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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Air discharges isentropically on a supersonic wind tunnel which is designed to achieve supersonic flow on the test section. It can be done by choking the air at the throat of a converging-diverging nozzle, wherein at the throat, the local speed is equal to the speed of sound. At the reservoir, the pressure and temperature are 500 kilopascals and 882 Kelvin, respectively. If the flow rate along the nozzle is constant at 170.1 kg/s, compute for the area at the throat.
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