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Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2. / Kosinov, A. D.; Kolosov, G. L.; Semionov, N. V. et al.

In: Physics of Fluids, Vol. 28, No. 6, 064101, 01.06.2016.

Research output: Contribution to journal › Article › peer-review

Harvard

Kosinov, AD, Kolosov, GL, Semionov, NV & Yermolaev, YG 2016, 'Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2', Physics of Fluids, vol. 28, no. 6, 064101. https://doi.org/10.1063/1.4952999

APA

Kosinov, A. D., Kolosov, G. L., Semionov, N. V., & Yermolaev, Y. G. (2016). Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2. Physics of Fluids, 28(6), [064101]. https://doi.org/10.1063/1.4952999

Vancouver

Kosinov AD, Kolosov GL, Semionov NV, Yermolaev YG. Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2. Physics of Fluids. 2016 Jun 1;28(6):064101. doi: 10.1063/1.4952999

Author

Kosinov, A. D. ; Kolosov, G. L. ; Semionov, N. V. et al. / Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2. In: Physics of Fluids. 2016 ; Vol. 28, No. 6.

BibTeX

@article{2e5334aac25d4f4c9fb5db4fdbbb233c,
title = "Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2",
abstract = "Experimental results are presented on the linear development of a wave train in a three-dimensional supersonic boundary layer on a swept wing with 45°-sweep angle at Mach number M = 2.0. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at frequencies 10 and 20 kHz. The maximum of the controlled pulsation amplitude was localized in the boundary layer in normal to the swept-wing surface direction for spatial amplitude distributions as well as for the amplitude wave spectra. The asymmetry of the wave characteristics of the unstable disturbances in the boundary layer of a swept wing caused by the presence of crossflow is confirmed. The stability characteristics, including dispersion relations and amplification rates over a wide range of wave inclination angles, are obtained for disturbances with prescribed frequencies 10 and 20 kHz.",
author = "Kosinov, {A. D.} and Kolosov, {G. L.} and Semionov, {N. V.} and Yermolaev, {Yu G.}",
year = "2016",
month = jun,
day = "1",
doi = "10.1063/1.4952999",
language = "English",
volume = "28",
journal = "Physics of Fluids",
issn = "1070-6631",
publisher = "American Institute of Physics",
number = "6",

}

RIS

TY - JOUR

T1 - Linear development of controlled disturbances in the supersonic boundary layer on a swept wing at Mach 2

AU - Kosinov, A. D.

AU - Kolosov, G. L.

AU - Semionov, N. V.

AU - Yermolaev, Yu G.

PY - 2016/6/1

Y1 - 2016/6/1

N2 - Experimental results are presented on the linear development of a wave train in a three-dimensional supersonic boundary layer on a swept wing with 45°-sweep angle at Mach number M = 2.0. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at frequencies 10 and 20 kHz. The maximum of the controlled pulsation amplitude was localized in the boundary layer in normal to the swept-wing surface direction for spatial amplitude distributions as well as for the amplitude wave spectra. The asymmetry of the wave characteristics of the unstable disturbances in the boundary layer of a swept wing caused by the presence of crossflow is confirmed. The stability characteristics, including dispersion relations and amplification rates over a wide range of wave inclination angles, are obtained for disturbances with prescribed frequencies 10 and 20 kHz.

AB - Experimental results are presented on the linear development of a wave train in a three-dimensional supersonic boundary layer on a swept wing with 45°-sweep angle at Mach number M = 2.0. Artificial disturbances in the boundary layer were excited by periodical glow discharge mainly at frequencies 10 and 20 kHz. The maximum of the controlled pulsation amplitude was localized in the boundary layer in normal to the swept-wing surface direction for spatial amplitude distributions as well as for the amplitude wave spectra. The asymmetry of the wave characteristics of the unstable disturbances in the boundary layer of a swept wing caused by the presence of crossflow is confirmed. The stability characteristics, including dispersion relations and amplification rates over a wide range of wave inclination angles, are obtained for disturbances with prescribed frequencies 10 and 20 kHz.

UR - http://www.scopus.com/inward/record.url?scp=84974622146&partnerID=8YFLogxK

U2 - 10.1063/1.4952999

DO - 10.1063/1.4952999

M3 - Article

AN - SCOPUS:84974622146

VL - 28

JO - Physics of Fluids

JF - Physics of Fluids

SN - 1070-6631

IS - 6

M1 - 064101

ER -

ID: 25838761