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The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2. / Semionov, N. V.; Yermolaev, Yu G.; Kosinov, A. D. et al.

Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017: Dedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS. ed. / Fomin. Vol. 1893 American Institute of Physics Inc., 2017. 030086 (AIP Conference Proceedings; Vol. 1893).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Research › peer-review

Harvard

Semionov, NV, Yermolaev, YG, Kosinov, AD, Semenov, AN, Smorodsky, BV & Yatskikh, AA 2017, The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2. in Fomin (ed.), Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017: Dedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS. vol. 1893, 030086, AIP Conference Proceedings, vol. 1893, American Institute of Physics Inc., 25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017, Novosibirsk, Russian Federation, 05.06.2017. https://doi.org/10.1063/1.5007544

APA

Semionov, N. V., Yermolaev, Y. G., Kosinov, A. D., Semenov, A. N., Smorodsky, B. V., & Yatskikh, A. A. (2017). The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2. In Fomin (Ed.), Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017: Dedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS (Vol. 1893). [030086] (AIP Conference Proceedings; Vol. 1893). American Institute of Physics Inc.. https://doi.org/10.1063/1.5007544

Vancouver

Semionov NV, Yermolaev YG, Kosinov AD, Semenov AN, Smorodsky BV, Yatskikh AA. The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2. In Fomin, editor, Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017: Dedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS. Vol. 1893. American Institute of Physics Inc. 2017. 030086. (AIP Conference Proceedings). doi: 10.1063/1.5007544

Author

Semionov, N. V. ; Yermolaev, Yu G. ; Kosinov, A. D. et al. / The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2. Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017: Dedicated to the 60th Anniversary of the Khristianovich Institute of Theoretical and Applied Mechanics SB RAS. editor / Fomin. Vol. 1893 American Institute of Physics Inc., 2017. (AIP Conference Proceedings).

BibTeX

@inproceedings{0d330579cd4347b8b5ea50212696d01b,
title = "The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2",
abstract = "The paper is devoted to an experimental and theoretical study of effect of small angle of attack on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach number M=2. The experiments are conducted at the low nose supersonic wind tunnel T-325 of ITAM. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. The transition location is determined using a hot-wire anemometer. Confirmed monotonous growth of the transition Reynolds numbers with increasing of angle of attack from -2°to 2.5°. The experimental data on the influence of the angle of attack on the disturbances evolution in the supersonic boundary layer on the swept wing model are obtained. Calculations on the effect of small angles of attack on the development of perturbations are made in the framework of the linear theory of stability. A good qualitative correspondence of theoretical and experimental data are obtained.",
keywords = "CROSS-FLOW VORTICES",
author = "Semionov, {N. V.} and Yermolaev, {Yu G.} and Kosinov, {A. D.} and Semenov, {A. N.} and Smorodsky, {B. V.} and Yatskikh, {A. A.}",
year = "2017",
month = oct,
day = "26",
doi = "10.1063/1.5007544",
language = "English",
volume = "1893",
series = "AIP Conference Proceedings",
publisher = "American Institute of Physics Inc.",
editor = "Fomin",
booktitle = "Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017",
note = "25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017 ; Conference date: 05-06-2017 Through 09-06-2017",

}

RIS

TY - GEN

T1 - The effect of small angle of attack on the laminar-turbulent transition in boundary layer on swept wing at Mach number M=2

AU - Semionov, N. V.

AU - Yermolaev, Yu G.

AU - Kosinov, A. D.

AU - Semenov, A. N.

AU - Smorodsky, B. V.

AU - Yatskikh, A. A.

PY - 2017/10/26

Y1 - 2017/10/26

N2 - The paper is devoted to an experimental and theoretical study of effect of small angle of attack on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach number M=2. The experiments are conducted at the low nose supersonic wind tunnel T-325 of ITAM. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. The transition location is determined using a hot-wire anemometer. Confirmed monotonous growth of the transition Reynolds numbers with increasing of angle of attack from -2°to 2.5°. The experimental data on the influence of the angle of attack on the disturbances evolution in the supersonic boundary layer on the swept wing model are obtained. Calculations on the effect of small angles of attack on the development of perturbations are made in the framework of the linear theory of stability. A good qualitative correspondence of theoretical and experimental data are obtained.

AB - The paper is devoted to an experimental and theoretical study of effect of small angle of attack on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach number M=2. The experiments are conducted at the low nose supersonic wind tunnel T-325 of ITAM. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. The transition location is determined using a hot-wire anemometer. Confirmed monotonous growth of the transition Reynolds numbers with increasing of angle of attack from -2°to 2.5°. The experimental data on the influence of the angle of attack on the disturbances evolution in the supersonic boundary layer on the swept wing model are obtained. Calculations on the effect of small angles of attack on the development of perturbations are made in the framework of the linear theory of stability. A good qualitative correspondence of theoretical and experimental data are obtained.

KW - CROSS-FLOW VORTICES

UR - http://www.scopus.com/inward/record.url?scp=85034262297&partnerID=8YFLogxK

U2 - 10.1063/1.5007544

DO - 10.1063/1.5007544

M3 - Conference contribution

AN - SCOPUS:85034262297

VL - 1893

T3 - AIP Conference Proceedings

BT - Proceedings of the XXV Conference on High-Energy Processes in Condensed Matter, HEPCM 2017

A2 - Fomin, null

PB - American Institute of Physics Inc.

T2 - 25th Conference on High-Energy Processes in Condensed Matter, HEPCM 2017

Y2 - 5 June 2017 through 9 June 2017

ER -

ID: 9695977