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Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow. / Ermolaev, Yu G.; Kosinov, A. D.; Semenov, A. N. et al.

In: Thermophysics and Aeromechanics, Vol. 25, No. 5, 01.09.2018, p. 659-665.

Research output: Contribution to journal › Article › peer-review

Harvard

Ermolaev, YG, Kosinov, AD, Semenov, AN, Semionov, NV & Yatskikh, AA 2018, 'Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow', Thermophysics and Aeromechanics, vol. 25, no. 5, pp. 659-665. https://doi.org/10.1134/S0869864318050025

APA

Ermolaev, Y. G., Kosinov, A. D., Semenov, A. N., Semionov, N. V., & Yatskikh, A. A. (2018). Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow. Thermophysics and Aeromechanics, 25(5), 659-665. https://doi.org/10.1134/S0869864318050025

Vancouver

Ermolaev YG, Kosinov AD, Semenov AN, Semionov NV, Yatskikh AA. Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow. Thermophysics and Aeromechanics. 2018 Sept 1;25(5):659-665. doi: 10.1134/S0869864318050025

Author

Ermolaev, Yu G. ; Kosinov, A. D. ; Semenov, A. N. et al. / Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow. In: Thermophysics and Aeromechanics. 2018 ; Vol. 25, No. 5. pp. 659-665.

BibTeX

@article{4bd44a7428bf482c893193cd2ba6cfda,
title = "Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow",
abstract = "An experimental study of the influence of unit Reynolds number on the position of laminar-turbulent transition in swept-wing boundary layer at supersonic flow velocities was carried out. In the experiments, a swept-wing model with 3-% circular arc airfoil and 45-deg gliding angle of wing edges was used. The position of the transition was iden-tified using a hot-wire anemometer. It was found that at М = 2 and 2.5, an increase in the unit Reynolds number (Re1) leads to a transition delay. It was shown that an increase in freestream Mach number and in the level of flow pulsations in the wind-tunnel test section leads to a less pronounced influence of Re1 on the transition position. At a high noise level due to the growth of Mach number or due to the introduction of vortical disturbances, no effect due to unit Reyn-olds number on the transition position was observed.",
keywords = "laminar-turbulent transition, supersonic boundary layer, swept wing, unit Reynolds number, BOUNDARY-LAYER, NOISE",
author = "Ermolaev, {Yu G.} and Kosinov, {A. D.} and Semenov, {A. N.} and Semionov, {N. V.} and Yatskikh, {A. A.}",
year = "2018",
month = sep,
day = "1",
doi = "10.1134/S0869864318050025",
language = "English",
volume = "25",
pages = "659--665",
journal = "Thermophysics and Aeromechanics",
issn = "0869-8643",
publisher = "PLEIADES PUBLISHING INC",
number = "5",

}

RIS

TY - JOUR

T1 - Effect of unit Reynolds number on the laminar-turbulent transition on a swept wing in supersonic flow

AU - Ermolaev, Yu G.

AU - Kosinov, A. D.

AU - Semenov, A. N.

AU - Semionov, N. V.

AU - Yatskikh, A. A.

PY - 2018/9/1

Y1 - 2018/9/1

N2 - An experimental study of the influence of unit Reynolds number on the position of laminar-turbulent transition in swept-wing boundary layer at supersonic flow velocities was carried out. In the experiments, a swept-wing model with 3-% circular arc airfoil and 45-deg gliding angle of wing edges was used. The position of the transition was iden-tified using a hot-wire anemometer. It was found that at М = 2 and 2.5, an increase in the unit Reynolds number (Re1) leads to a transition delay. It was shown that an increase in freestream Mach number and in the level of flow pulsations in the wind-tunnel test section leads to a less pronounced influence of Re1 on the transition position. At a high noise level due to the growth of Mach number or due to the introduction of vortical disturbances, no effect due to unit Reyn-olds number on the transition position was observed.

AB - An experimental study of the influence of unit Reynolds number on the position of laminar-turbulent transition in swept-wing boundary layer at supersonic flow velocities was carried out. In the experiments, a swept-wing model with 3-% circular arc airfoil and 45-deg gliding angle of wing edges was used. The position of the transition was iden-tified using a hot-wire anemometer. It was found that at М = 2 and 2.5, an increase in the unit Reynolds number (Re1) leads to a transition delay. It was shown that an increase in freestream Mach number and in the level of flow pulsations in the wind-tunnel test section leads to a less pronounced influence of Re1 on the transition position. At a high noise level due to the growth of Mach number or due to the introduction of vortical disturbances, no effect due to unit Reyn-olds number on the transition position was observed.

KW - laminar-turbulent transition

KW - supersonic boundary layer

KW - swept wing

KW - unit Reynolds number

KW - BOUNDARY-LAYER

KW - NOISE

UR - http://www.scopus.com/inward/record.url?scp=85059053061&partnerID=8YFLogxK

U2 - 10.1134/S0869864318050025

DO - 10.1134/S0869864318050025

M3 - Article

AN - SCOPUS:85059053061

VL - 25

SP - 659

EP - 665

JO - Thermophysics and Aeromechanics

JF - Thermophysics and Aeromechanics

SN - 0869-8643

IS - 5

ER -

ID: 18144037