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Regimes of flow turbulization near swept wing edge in hypersonic flow. / Vaganov, A. V.; Kosinov, A. D.; Noev, A. Yu и др.

19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. ред. / Vasily Fomin. American Institute of Physics Inc., 2018. 030112 (AIP Conference Proceedings; Том 2027).

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

Harvard

Vaganov, AV, Kosinov, AD, Noev, AY, Radchenko, VN & Skuratov, AS 2018, Regimes of flow turbulization near swept wing edge in hypersonic flow. в V Fomin (ред.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018., 030112, AIP Conference Proceedings, Том. 2027, American Institute of Physics Inc., 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018, Akademgorodok, Novosibirsk, Российская Федерация, 13.08.2018. https://doi.org/10.1063/1.5065206

APA

Vaganov, A. V., Kosinov, A. D., Noev, A. Y., Radchenko, V. N., & Skuratov, A. S. (2018). Regimes of flow turbulization near swept wing edge in hypersonic flow. в V. Fomin (Ред.), 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 [030112] (AIP Conference Proceedings; Том 2027). American Institute of Physics Inc.. https://doi.org/10.1063/1.5065206

Vancouver

Vaganov AV, Kosinov AD, Noev AY, Radchenko VN, Skuratov AS. Regimes of flow turbulization near swept wing edge in hypersonic flow. в Fomin V, Редактор, 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. American Institute of Physics Inc. 2018. 030112. (AIP Conference Proceedings). doi: 10.1063/1.5065206

Author

Vaganov, A. V. ; Kosinov, A. D. ; Noev, A. Yu и др. / Regimes of flow turbulization near swept wing edge in hypersonic flow. 19th International Conference on the Methods of Aerophysical Research, ICMAR 2018. Редактор / Vasily Fomin. American Institute of Physics Inc., 2018. (AIP Conference Proceedings).

BibTeX

@inproceedings{5fc57e965ef140888d91917478c5631a,
title = "Regimes of flow turbulization near swept wing edge in hypersonic flow",
abstract = "Experiments were conducted at Mach number 6 in UT-1M Ludwieg tube. The model is flat delta plate with blunt swept (χ=75-67°) edges and sharp tip. Surface heat transfer distributions were obtained using luminescent temperature converters. Characteristic zones and features of the flow are explored in the presence of natural as well as artificial disturbances namely surface roughness and N-wave falling on the edge. Quantitative data on attachment line heat transfer are obtained depending on various parameters.",
keywords = "ATTACHMENT-LINE, TRANSITION",
author = "Vaganov, {A. V.} and Kosinov, {A. D.} and Noev, {A. Yu} and Radchenko, {V. N.} and Skuratov, {A. S.}",
year = "2018",
month = nov,
day = "2",
doi = "10.1063/1.5065206",
language = "English",
series = "AIP Conference Proceedings",
publisher = "American Institute of Physics Inc.",
editor = "Vasily Fomin",
booktitle = "19th International Conference on the Methods of Aerophysical Research, ICMAR 2018",
note = "19th International Conference on the Methods of Aerophysical Research, ICMAR 2018 ; Conference date: 13-08-2018 Through 19-08-2018",

}

RIS

TY - GEN

T1 - Regimes of flow turbulization near swept wing edge in hypersonic flow

AU - Vaganov, A. V.

AU - Kosinov, A. D.

AU - Noev, A. Yu

AU - Radchenko, V. N.

AU - Skuratov, A. S.

PY - 2018/11/2

Y1 - 2018/11/2

N2 - Experiments were conducted at Mach number 6 in UT-1M Ludwieg tube. The model is flat delta plate with blunt swept (χ=75-67°) edges and sharp tip. Surface heat transfer distributions were obtained using luminescent temperature converters. Characteristic zones and features of the flow are explored in the presence of natural as well as artificial disturbances namely surface roughness and N-wave falling on the edge. Quantitative data on attachment line heat transfer are obtained depending on various parameters.

AB - Experiments were conducted at Mach number 6 in UT-1M Ludwieg tube. The model is flat delta plate with blunt swept (χ=75-67°) edges and sharp tip. Surface heat transfer distributions were obtained using luminescent temperature converters. Characteristic zones and features of the flow are explored in the presence of natural as well as artificial disturbances namely surface roughness and N-wave falling on the edge. Quantitative data on attachment line heat transfer are obtained depending on various parameters.

KW - ATTACHMENT-LINE

KW - TRANSITION

UR - http://www.scopus.com/inward/record.url?scp=85056340306&partnerID=8YFLogxK

U2 - 10.1063/1.5065206

DO - 10.1063/1.5065206

M3 - Conference contribution

AN - SCOPUS:85056340306

T3 - AIP Conference Proceedings

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

A2 - Fomin, Vasily

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: 25837618