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An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2. / Semionov, N. V.; Yermolaev, Yu G.; Kocharin, V. L. et al.

19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. ed. / Fomin. Vol. 2027 American Institute of Physics Inc., 2018. 030156 (AIP Conference Proceedings; Vol. 2027).

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

Harvard

Semionov, NV, Yermolaev, YG, Kocharin, VL, Kosinov, AD, Semenov, AN, Smorodsky, BV & Yatskikh, AA 2018, An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2. in Fomin (ed.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. vol. 2027, 030156, AIP Conference Proceedings, vol. 2027, American Institute of Physics Inc., 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018, Akademgorodok, Novosibirsk, Russian Federation, 13.08.2018. https://doi.org/10.1063/1.5065250

APA

Semionov, N. V., Yermolaev, Y. G., Kocharin, V. L., Kosinov, A. D., Semenov, A. N., Smorodsky, B. V., & Yatskikh, A. A. (2018). An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2. In Fomin (Ed.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 (Vol. 2027). [030156] (AIP Conference Proceedings; Vol. 2027). American Institute of Physics Inc.. https://doi.org/10.1063/1.5065250

Vancouver

Semionov NV, Yermolaev YG, Kocharin VL, Kosinov AD, Semenov AN, Smorodsky BV et al. An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2. In Fomin, editor, 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. Vol. 2027. American Institute of Physics Inc. 2018. 030156. (AIP Conference Proceedings). doi: 10.1063/1.5065250

Author

Semionov, N. V. ; Yermolaev, Yu G. ; Kocharin, V. L. et al. / An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2. 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. editor / Fomin. Vol. 2027 American Institute of Physics Inc., 2018. (AIP Conference Proceedings).

BibTeX

@inproceedings{2b12dbb8bbc64bcf82d1def0445ea57e,
title = "An effect of small angle of attack on disturbances evolution in swept wing boundary layer 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. The experiments were conducted at the low nose supersonic wind tunnel T-325 of ITAM at Mach numbers M=2. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. 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. Obtained good qualitative correspondence of experimental transition Reynolds number and the calculated dependences obtained for different values of the N factor. For the first time a comparison of the experimental growth rates with the results of calculations for various angles of attack was made. A good agreement between the experimental and theoretical data for the zero angle of attack was obtained. At the same time, there was no such agreement at non-zero angles of attack.",
keywords = "TRANSITION, STABILITY",
author = "Semionov, {N. V.} and Yermolaev, {Yu G.} and Kocharin, {V. L.} and Kosinov, {A. D.} and Semenov, {A. N.} and Smorodsky, {B. V.} and Yatskikh, {A. A.}",
note = "Publisher Copyright: {\textcopyright} 2018 Author(s).; 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 ; Conference date: 13-08-2018 Through 19-08-2018",
year = "2018",
month = nov,
day = "2",
doi = "10.1063/1.5065250",
language = "English",
volume = "2027",
series = "AIP Conference Proceedings",
publisher = "American Institute of Physics Inc.",
editor = "Fomin",
booktitle = "19th International Conference on the Methods of Aerophysical Research, ICMAR 2018",

}

RIS

TY - GEN

T1 - An effect of small angle of attack on disturbances evolution in swept wing boundary layer at Mach number M=2

AU - Semionov, N. V.

AU - Yermolaev, Yu G.

AU - Kocharin, V. L.

AU - Kosinov, A. D.

AU - Semenov, A. N.

AU - Smorodsky, B. V.

AU - Yatskikh, A. A.

N1 - Publisher Copyright: © 2018 Author(s).

PY - 2018/11/2

Y1 - 2018/11/2

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. The experiments were conducted at the low nose supersonic wind tunnel T-325 of ITAM at Mach numbers M=2. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. 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. Obtained good qualitative correspondence of experimental transition Reynolds number and the calculated dependences obtained for different values of the N factor. For the first time a comparison of the experimental growth rates with the results of calculations for various angles of attack was made. A good agreement between the experimental and theoretical data for the zero angle of attack was obtained. At the same time, there was no such agreement at non-zero angles of attack.

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. The experiments were conducted at the low nose supersonic wind tunnel T-325 of ITAM at Mach numbers M=2. Model is a symmetrical wing with a 45°sweep angle, a 3 percent-thick circular-arc airfoil. 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. Obtained good qualitative correspondence of experimental transition Reynolds number and the calculated dependences obtained for different values of the N factor. For the first time a comparison of the experimental growth rates with the results of calculations for various angles of attack was made. A good agreement between the experimental and theoretical data for the zero angle of attack was obtained. At the same time, there was no such agreement at non-zero angles of attack.

KW - TRANSITION

KW - STABILITY

UR - http://www.scopus.com/inward/record.url?scp=85056316351&partnerID=8YFLogxK

U2 - 10.1063/1.5065250

DO - 10.1063/1.5065250

M3 - Conference contribution

AN - SCOPUS:85056316351

VL - 2027

T3 - AIP Conference Proceedings

BT - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018

A2 - Fomin, null

PB - American Institute of Physics Inc.

T2 - 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018

Y2 - 13 August 2018 through 19 August 2018

ER -

ID: 17413182