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Experimental-theoretical study of pressure distribution along the wall when a supersonic gas flow moves in an axisymmetric channel with sudden expansion

Experimental-theoretical study of pressure distribution along the wall when a supersonic gas flow... The paper describes a study of pressure distribution along the wall of an axisymmetric channel with a straight step. A supersonic gas flow formed inside the channel when an external flow with Mach numbers M = 5 and M = 6 moves around an axisymmetric model with internal duct is considered. A supersonic aerodynamic wind tunnel of a short-term action is used for experiments. The results of measuring the pressure along the channel wall in the flow around the model under study are presented. The data of aerodynamic tests are compared with the results of numerical calculations, and the resulting pressure distributions are compared. It has been established that the nonmonotonic nature of a change in pressure along the wall is caused by the shock waves, which accompany the supersonic gas flow in the channel. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

Experimental-theoretical study of pressure distribution along the wall when a supersonic gas flow moves in an axisymmetric channel with sudden expansion

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Publisher
Springer Journals
Copyright
Copyright © N.P. Skibina, S.A. Tyrtyshny, and V.V. Faraponov 2022
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/s0869864322010061
Publisher site
See Article on Publisher Site

Abstract

The paper describes a study of pressure distribution along the wall of an axisymmetric channel with a straight step. A supersonic gas flow formed inside the channel when an external flow with Mach numbers M = 5 and M = 6 moves around an axisymmetric model with internal duct is considered. A supersonic aerodynamic wind tunnel of a short-term action is used for experiments. The results of measuring the pressure along the channel wall in the flow around the model under study are presented. The data of aerodynamic tests are compared with the results of numerical calculations, and the resulting pressure distributions are compared. It has been established that the nonmonotonic nature of a change in pressure along the wall is caused by the shock waves, which accompany the supersonic gas flow in the channel.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Jan 1, 2022

Keywords: aerodynamic tests; pressure recording; axisymmetric channel; shock waves

References