The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing

Standard

The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing. / Kosinov, Alexander; Semionov, Nikolai; Yermolaev, Yury и др.

в: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Том 234, № 1, 01.01.2020, стр. 96-101.

Результаты исследований: Научные публикации в периодических изданиях › статья › Рецензирование

Harvard

Kosinov, A, Semionov, N, Yermolaev, Y, Smorodsky, B, Kolosov, G, Yatskikh, A & Semenov, A 2020, 'The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing', Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, Том. 234, № 1, стр. 96-101. https://doi.org/10.1177/0954410019852804

APA

Kosinov, A., Semionov, N., Yermolaev, Y., Smorodsky, B., Kolosov, G., Yatskikh, A., & Semenov, A. (2020). The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, 234(1), 96-101. https://doi.org/10.1177/0954410019852804

Vancouver

Kosinov A, Semionov N, Yermolaev Y, Smorodsky B, Kolosov G, Yatskikh A и др. The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. 2020 янв. 1;234(1):96-101. doi: 10.1177/0954410019852804

Author

Kosinov, Alexander ; Semionov, Nikolai ; Yermolaev, Yury и др. / The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing. в: Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. 2020 ; Том 234, № 1. стр. 96-101.

BibTeX

@article{e36a9b1b2e4344439e395a65ffb3d803,

title = "The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing",

abstract = "The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.",

keywords = "angle of attack, experiment, hot-wire measurements, Supersonic boundary layer, swept wing, NUMBER, STABILITY",

author = "Alexander Kosinov and Nikolai Semionov and Yury Yermolaev and Boris Smorodsky and Gleb Kolosov and Aleksey Yatskikh and Alexander Semenov",

year = "2020",

month = jan,

day = "1",

doi = "10.1177/0954410019852804",

language = "English",

volume = "234",

pages = "96--101",

journal = "Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering",

issn = "0954-4100",

publisher = "SAGE Publications Ltd",

number = "1",

}

RIS

TY - JOUR

T1 - The influence of moderate angle-of-attack variation on disturbances evolution and transition to turbulence in supersonic boundary layer on swept wing

AU - Kosinov, Alexander

AU - Semionov, Nikolai

AU - Yermolaev, Yury

AU - Smorodsky, Boris

AU - Kolosov, Gleb

AU - Yatskikh, Aleksey

AU - Semenov, Alexander

PY - 2020/1/1

Y1 - 2020/1/1

N2 - The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.

AB - The paper is devoted to an experimental and theoretical study of effect of moderate angle-of-attack variation on disturbances evolution and laminar-turbulent transition in a supersonic boundary layer on swept wing at Mach 2. Monotonous growth of the transition Reynolds numbers with angle of attack increasing from −2° to 2.7° is confirmed. For the same conditions, calculations based on linear stability theory are performed. The experimental and computational results show a favourable comparison.

KW - angle of attack

KW - experiment

KW - hot-wire measurements

KW - Supersonic boundary layer

KW - swept wing

KW - NUMBER

KW - STABILITY

UR - http://www.scopus.com/inward/record.url?scp=85067801159&partnerID=8YFLogxK

U2 - 10.1177/0954410019852804

DO - 10.1177/0954410019852804

M3 - Article

AN - SCOPUS:85067801159

VL - 234

SP - 96

EP - 101

JO - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

JF - Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering

SN - 0954-4100

IS - 1

ER -

ID: 20655805