Evolution of artificial disturbances in swept wing supersonic boundary layer

G. L. Kolosov; A. V. Panina; A. D. Kosinov; V. S. Kosorygin; A. A. Yatskikh

doi:10.1088/1742-6596/1404/1/012084

Evolution of artificial disturbances in swept wing supersonic boundary layer

G. L. Kolosov, A. V. Panina, A. D. Kosinov, V. S. Kosorygin, A. A. Yatskikh

Research output: Contribution to journal › Conference article › peer-review

Abstract

Experimental data on the evolution of artificial controlled travelling disturbances in a three-dimensional supersonic boundary layer on a 45° swept wing at Mach number 2.0 is presented. Artificial disturbances were introduced in the boundary layer using a periodical glow discharge with a frequency of 20 kHz. Pulsations of the boundary layer were measured with a constant-temperature hot-wire anemometer and the probe moved parallel and not parallel to the leading edge of the model. In both cases spatial-temporal and spectral-wave characteristics of the wave train development were obtained and quantitatively compared with each other. This paper discusses the suitability of the method for measuring fluctuations fields when the probe is moving not parallel to the leading edge of the model.

Original language	English
Article number	012084
Journal	Journal of Physics: Conference Series
Volume	1404
Issue number	1
DOIs	https://doi.org/10.1088/1742-6596/1404/1/012084
Publication status	Published - 6 Dec 2019
Event	16th All-Russian Seminar with International Participation on Dynamics of Multiphase Media, DMM 2019 - Novosibirsk, Russian Federation Duration: 30 Sep 2019 → 5 Oct 2019

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title = "Evolution of artificial disturbances in swept wing supersonic boundary layer",

abstract = "Experimental data on the evolution of artificial controlled travelling disturbances in a three-dimensional supersonic boundary layer on a 45° swept wing at Mach number 2.0 is presented. Artificial disturbances were introduced in the boundary layer using a periodical glow discharge with a frequency of 20 kHz. Pulsations of the boundary layer were measured with a constant-temperature hot-wire anemometer and the probe moved parallel and not parallel to the leading edge of the model. In both cases spatial-temporal and spectral-wave characteristics of the wave train development were obtained and quantitatively compared with each other. This paper discusses the suitability of the method for measuring fluctuations fields when the probe is moving not parallel to the leading edge of the model.",

author = "Kolosov, {G. L.} and Panina, {A. V.} and Kosinov, {A. D.} and Kosorygin, {V. S.} and Yatskikh, {A. A.}",

note = "Publisher Copyright: {\textcopyright} 2019 IOP Publishing Ltd. Copyright: Copyright 2020 Elsevier B.V., All rights reserved.; 16th All-Russian Seminar with International Participation on Dynamics of Multiphase Media, DMM 2019 ; Conference date: 30-09-2019 Through 05-10-2019",

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AU - Kolosov, G. L.

AU - Panina, A. V.

AU - Kosinov, A. D.

AU - Kosorygin, V. S.

AU - Yatskikh, A. A.

PY - 2019/12/6

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N2 - Experimental data on the evolution of artificial controlled travelling disturbances in a three-dimensional supersonic boundary layer on a 45° swept wing at Mach number 2.0 is presented. Artificial disturbances were introduced in the boundary layer using a periodical glow discharge with a frequency of 20 kHz. Pulsations of the boundary layer were measured with a constant-temperature hot-wire anemometer and the probe moved parallel and not parallel to the leading edge of the model. In both cases spatial-temporal and spectral-wave characteristics of the wave train development were obtained and quantitatively compared with each other. This paper discusses the suitability of the method for measuring fluctuations fields when the probe is moving not parallel to the leading edge of the model.

AB - Experimental data on the evolution of artificial controlled travelling disturbances in a three-dimensional supersonic boundary layer on a 45° swept wing at Mach number 2.0 is presented. Artificial disturbances were introduced in the boundary layer using a periodical glow discharge with a frequency of 20 kHz. Pulsations of the boundary layer were measured with a constant-temperature hot-wire anemometer and the probe moved parallel and not parallel to the leading edge of the model. In both cases spatial-temporal and spectral-wave characteristics of the wave train development were obtained and quantitatively compared with each other. This paper discusses the suitability of the method for measuring fluctuations fields when the probe is moving not parallel to the leading edge of the model.

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VL - 1404

JO - Journal of Physics: Conference Series

JF - Journal of Physics: Conference Series

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T2 - 16th All-Russian Seminar with International Participation on Dynamics of Multiphase Media, DMM 2019

Y2 - 30 September 2019 through 5 October 2019

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Evolution of artificial disturbances in swept wing supersonic boundary layer

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