Evolution of artificial disturbances in swept wing supersonic boundary layer

Standard

Evolution of artificial disturbances in swept wing supersonic boundary layer. / Kolosov, G. L.; Panina, A. V.; Kosinov, A. D. et al.

In: Journal of Physics: Conference Series, Vol. 1404, No. 1, 012084, 06.12.2019.

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

Harvard

Kolosov, GL, Panina, AV, Kosinov, AD, Kosorygin, VS & Yatskikh, AA 2019, 'Evolution of artificial disturbances in swept wing supersonic boundary layer', Journal of Physics: Conference Series, vol. 1404, no. 1, 012084. https://doi.org/10.1088/1742-6596/1404/1/012084

APA

Kolosov, G. L., Panina, A. V., Kosinov, A. D., Kosorygin, V. S., & Yatskikh, A. A. (2019). Evolution of artificial disturbances in swept wing supersonic boundary layer. Journal of Physics: Conference Series, 1404(1), [012084]. https://doi.org/10.1088/1742-6596/1404/1/012084

Vancouver

Kolosov GL, Panina AV, Kosinov AD, Kosorygin VS, Yatskikh AA. Evolution of artificial disturbances in swept wing supersonic boundary layer. Journal of Physics: Conference Series. 2019 Dec 6;1404(1):012084. doi: 10.1088/1742-6596/1404/1/012084

Author

Kolosov, G. L. ; Panina, A. V. ; Kosinov, A. D. et al. / Evolution of artificial disturbances in swept wing supersonic boundary layer. In: Journal of Physics: Conference Series. 2019 ; Vol. 1404, No. 1.

BibTeX

@article{9e10a4be76444d34b7c7f329af6c8edf,

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",

year = "2019",

month = dec,

day = "6",

doi = "10.1088/1742-6596/1404/1/012084",

language = "English",

volume = "1404",

journal = "Journal of Physics: Conference Series",

issn = "1742-6588",

publisher = "IOP Publishing Ltd.",

number = "1",

}

RIS

TY - JOUR

T1 - Evolution of artificial disturbances in swept wing supersonic boundary layer

AU - Kolosov, G. L.

AU - Panina, A. V.

AU - Kosinov, A. D.

AU - Kosorygin, V. S.

AU - Yatskikh, A. A.

PY - 2019/12/6

Y1 - 2019/12/6

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.

UR - http://www.scopus.com/inward/record.url?scp=85077819452&partnerID=8YFLogxK

U2 - 10.1088/1742-6596/1404/1/012084

DO - 10.1088/1742-6596/1404/1/012084

M3 - Conference article

AN - SCOPUS:85077819452

VL - 1404

JO - Journal of Physics: Conference Series

JF - Journal of Physics: Conference Series

SN - 1742-6588

IS - 1

M1 - 012084

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

Y2 - 30 September 2019 through 5 October 2019

ER -

ID: 23120139