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Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition. / Gaponov, S. A.; Ermolaev, Yu G.; Zubkov, N. N. и др.

в: Fluid Dynamics, Том 52, № 6, 01.11.2017, стр. 769-776.

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

Harvard

Gaponov, SA, Ermolaev, YG, Zubkov, NN, Kosinov, AD, Lysenko, VI, Smorodskii, BV & Yatskikh, AA 2017, 'Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition', Fluid Dynamics, Том. 52, № 6, стр. 769-776. https://doi.org/10.1134/S0015462817060052

APA

Gaponov, S. A., Ermolaev, Y. G., Zubkov, N. N., Kosinov, A. D., Lysenko, V. I., Smorodskii, B. V., & Yatskikh, A. A. (2017). Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition. Fluid Dynamics, 52(6), 769-776. https://doi.org/10.1134/S0015462817060052

Vancouver

Gaponov SA, Ermolaev YG, Zubkov NN, Kosinov AD, Lysenko VI, Smorodskii BV и др. Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition. Fluid Dynamics. 2017 нояб. 1;52(6):769-776. doi: 10.1134/S0015462817060052

Author

Gaponov, S. A. ; Ermolaev, Yu G. ; Zubkov, N. N. и др. / Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition. в: Fluid Dynamics. 2017 ; Том 52, № 6. стр. 769-776.

BibTeX

@article{9686f80ff9bc49a5b3927a067205723b,
title = "Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition",
abstract = "The effect of distributed tangential injection of heavy SF6 gas into the wall zone of a boundary layer on the supersonic flow stability and laminar-turbulent transition is experimentally and theoretically investigated at the freestream Mach number M∞ = 2. For the first time it is experimentally shown that in the case of this injection laminar-turbulent transition is downstream displaced.",
keywords = "compressible boundary layer, hydrodynamic stability, injection, laminar-turbulent transition, permeable surface, PERMEABILITY, STABILITY, ROUGHNESS",
author = "Gaponov, {S. A.} and Ermolaev, {Yu G.} and Zubkov, {N. N.} and Kosinov, {A. D.} and Lysenko, {V. I.} and Smorodskii, {B. V.} and Yatskikh, {A. A.}",
year = "2017",
month = nov,
day = "1",
doi = "10.1134/S0015462817060052",
language = "English",
volume = "52",
pages = "769--776",
journal = "Fluid Dynamics",
issn = "0015-4628",
publisher = "Maik Nauka-Interperiodica Publishing",
number = "6",

}

RIS

TY - JOUR

T1 - Investigation of the effect of heavy gas injection into a supersonic boundary layer on laminar-turbulent transition

AU - Gaponov, S. A.

AU - Ermolaev, Yu G.

AU - Zubkov, N. N.

AU - Kosinov, A. D.

AU - Lysenko, V. I.

AU - Smorodskii, B. V.

AU - Yatskikh, A. A.

PY - 2017/11/1

Y1 - 2017/11/1

N2 - The effect of distributed tangential injection of heavy SF6 gas into the wall zone of a boundary layer on the supersonic flow stability and laminar-turbulent transition is experimentally and theoretically investigated at the freestream Mach number M∞ = 2. For the first time it is experimentally shown that in the case of this injection laminar-turbulent transition is downstream displaced.

AB - The effect of distributed tangential injection of heavy SF6 gas into the wall zone of a boundary layer on the supersonic flow stability and laminar-turbulent transition is experimentally and theoretically investigated at the freestream Mach number M∞ = 2. For the first time it is experimentally shown that in the case of this injection laminar-turbulent transition is downstream displaced.

KW - compressible boundary layer

KW - hydrodynamic stability

KW - injection

KW - laminar-turbulent transition

KW - permeable surface

KW - PERMEABILITY

KW - STABILITY

KW - ROUGHNESS

UR - http://www.scopus.com/inward/record.url?scp=85040968386&partnerID=8YFLogxK

U2 - 10.1134/S0015462817060052

DO - 10.1134/S0015462817060052

M3 - Article

AN - SCOPUS:85040968386

VL - 52

SP - 769

EP - 776

JO - Fluid Dynamics

JF - Fluid Dynamics

SN - 0015-4628

IS - 6

ER -

ID: 25837911