Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2

Standard

Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2. / Semionov, N. V.; Kosinov, A. D.; Yermolaev, Yu G. и др.

High-Energy Processes in Condensed Matter, HEPCM 2020: Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter, Dedicated to the 90th Anniversary of the Birth of RI Soloukhin. ред. / Vasily M. Fomin. American Institute of Physics Inc., 2020. 030062 (AIP Conference Proceedings; Том 2288).

Результаты исследований: Публикации в книгах, отчётах, сборниках, трудах конференций › статья в сборнике материалов конференции › научная › Рецензирование

Harvard

Semionov, NV, Kosinov, AD , Yermolaev, YG, Kocharin, VL, Shipul, SA & Yatskikh, AA 2020, Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2. в VM Fomin (ред.), High-Energy Processes in Condensed Matter, HEPCM 2020: Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter, Dedicated to the 90th Anniversary of the Birth of RI Soloukhin., 030062, AIP Conference Proceedings, Том. 2288, American Institute of Physics Inc., 27th Conference on High-Energy Processes in Condensed Matter, HEPCM 2020, Novosibirsk, Российская Федерация, 29.06.2020. https://doi.org/10.1063/5.0028295

APA

Semionov, N. V., Kosinov, A. D., Yermolaev, Y. G., Kocharin, V. L., Shipul, S. A., & Yatskikh, A. A. (2020). Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2. в V. M. Fomin (Ред.), High-Energy Processes in Condensed Matter, HEPCM 2020: Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter, Dedicated to the 90th Anniversary of the Birth of RI Soloukhin [030062] (AIP Conference Proceedings; Том 2288). American Institute of Physics Inc.. https://doi.org/10.1063/5.0028295

Vancouver

Semionov NV, Kosinov AD , Yermolaev YG, Kocharin VL, Shipul SA, Yatskikh AA. Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2. в Fomin VM, Редактор, High-Energy Processes in Condensed Matter, HEPCM 2020: Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter, Dedicated to the 90th Anniversary of the Birth of RI Soloukhin. American Institute of Physics Inc. 2020. 030062. (AIP Conference Proceedings). doi: 10.1063/5.0028295

Author

Semionov, N. V. ; Kosinov, A. D. ; Yermolaev, Yu G. и др. / Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2. High-Energy Processes in Condensed Matter, HEPCM 2020: Proceedings of the XXVII Conference on High-Energy Processes in Condensed Matter, Dedicated to the 90th Anniversary of the Birth of RI Soloukhin. Редактор / Vasily M. Fomin. American Institute of Physics Inc., 2020. (AIP Conference Proceedings).

BibTeX

@inproceedings{b1e7a2f75785414d8dcd999540840dbd,

title = "Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2",

abstract = "The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.",

keywords = "BOUNDARY-LAYER, NUMBER",

author = "Semionov, {N. V.} and Kosinov, {A. D.} and Yermolaev, {Yu G.} and Kocharin, {V. L.} and Shipul, {S. A.} and Yatskikh, {A. A.}",

note = "Publisher Copyright: {\textcopyright} 2020 Author(s). Copyright: Copyright 2020 Elsevier B.V., All rights reserved.; 27th Conference on High-Energy Processes in Condensed Matter, HEPCM 2020 ; Conference date: 29-06-2020 Through 03-07-2020",

year = "2020",

month = oct,

day = "26",

doi = "10.1063/5.0028295",

language = "English",

series = "AIP Conference Proceedings",

publisher = "American Institute of Physics Inc.",

editor = "Fomin, {Vasily M.}",

booktitle = "High-Energy Processes in Condensed Matter, HEPCM 2020",

}

RIS

TY - GEN

T1 - Influence of small attack angles on the transition on the wing with the subsonic leading edge at M=2

AU - Semionov, N. V.

AU - Kosinov, A. D.

AU - Yermolaev, Yu G.

AU - Kocharin, V. L.

AU - Shipul, S. A.

AU - Yatskikh, A. A.

PY - 2020/10/26

Y1 - 2020/10/26

N2 - The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.

AB - The paper is devoted to an experimental study of laminar-turbulent transition in supersonic boundary layers on swept wings. The experiments were fulfilled in the low nose supersonic wind tunnel T-325 of Khristianovich Institute of Theoretical and Applied Mechanics on the models of a swept wing with a swept angle of 72° at Mach 2 which corresponds to a subsonic leading edge. The transition location was determined using a constant temperature hot-wire anemometer. A comparison of the influence of small angles of attack on the transition position with a model with a supersonic leading edge is shown. The transition to a wing model with a subsonic leading edge occurs earlier than on a wing model with a supersonic leading edge. The angle of attack has a significant effect on the position of the transition point from the laminar to turbulent flow. The data presented in the article are among the first results for a swept wing with a subsonic leading edge.

KW - BOUNDARY-LAYER

KW - NUMBER

UR - http://www.scopus.com/inward/record.url?scp=85096637189&partnerID=8YFLogxK

U2 - 10.1063/5.0028295

DO - 10.1063/5.0028295

M3 - Conference contribution

AN - SCOPUS:85096637189

T3 - AIP Conference Proceedings

BT - High-Energy Processes in Condensed Matter, HEPCM 2020

A2 - Fomin, Vasily M.

PB - American Institute of Physics Inc.

T2 - 27th Conference on High-Energy Processes in Condensed Matter, HEPCM 2020

Y2 - 29 June 2020 through 3 July 2020

ER -

ID: 26098223