Standard

Impact of incident Mach wave on supersonic boundary layer. / Vaganov, A. V.; Ermolaev, Yu G.; Kolosov, G. L. et al.

In: Thermophysics and Aeromechanics, Vol. 23, No. 1, 01.01.2016, p. 43-48.

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

Harvard

Vaganov, AV, Ermolaev, YG, Kolosov, GL, Kosinov, AD, Panina, AV, Semionov, NV & Yatskikh, AA 2016, 'Impact of incident Mach wave on supersonic boundary layer', Thermophysics and Aeromechanics, vol. 23, no. 1, pp. 43-48. https://doi.org/10.1134/S0869864316010054

APA

Vaganov, A. V., Ermolaev, Y. G., Kolosov, G. L., Kosinov, A. D., Panina, A. V., Semionov, N. V., & Yatskikh, A. A. (2016). Impact of incident Mach wave on supersonic boundary layer. Thermophysics and Aeromechanics, 23(1), 43-48. https://doi.org/10.1134/S0869864316010054

Vancouver

Vaganov AV, Ermolaev YG, Kolosov GL, Kosinov AD, Panina AV, Semionov NV et al. Impact of incident Mach wave on supersonic boundary layer. Thermophysics and Aeromechanics. 2016 Jan 1;23(1):43-48. doi: 10.1134/S0869864316010054

Author

Vaganov, A. V. ; Ermolaev, Yu G. ; Kolosov, G. L. et al. / Impact of incident Mach wave on supersonic boundary layer. In: Thermophysics and Aeromechanics. 2016 ; Vol. 23, No. 1. pp. 43-48.

BibTeX

@article{d8bfdd0061e640fdb75fd31a4c000cc7,
title = "Impact of incident Mach wave on supersonic boundary layer",
abstract = "Results of an experimental study of the excitation of high-intensity disturbances by a weak external shock wave in laminar boundary layer on flat-plate models with sharp and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker in turbulent boundary layer on the wall of wind-tunnel test section in the free stream is shown to have the form of an N-wave. It is found that, on the blunted plate, the intensity of pulsations produced by weak external shock waves in boundary layer several times exceeds the intensity of pulsations produced in boundary layer on the model with a sharp leading edge.",
keywords = "boundary layer, experimental studies, flat plate, hot-wire anemometry, sharp and blunt leading edges, supersonic velocities, wind tunnel",
author = "Vaganov, {A. V.} and Ermolaev, {Yu G.} and Kolosov, {G. L.} and Kosinov, {A. D.} and Panina, {A. V.} and Semionov, {N. V.} and Yatskikh, {A. A.}",
year = "2016",
month = jan,
day = "1",
doi = "10.1134/S0869864316010054",
language = "English",
volume = "23",
pages = "43--48",
journal = "Thermophysics and Aeromechanics",
issn = "0869-8643",
publisher = "PLEIADES PUBLISHING INC",
number = "1",

}

RIS

TY - JOUR

T1 - Impact of incident Mach wave on supersonic boundary layer

AU - Vaganov, A. V.

AU - Ermolaev, Yu G.

AU - Kolosov, G. L.

AU - Kosinov, A. D.

AU - Panina, A. V.

AU - Semionov, N. V.

AU - Yatskikh, A. A.

PY - 2016/1/1

Y1 - 2016/1/1

N2 - Results of an experimental study of the excitation of high-intensity disturbances by a weak external shock wave in laminar boundary layer on flat-plate models with sharp and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker in turbulent boundary layer on the wall of wind-tunnel test section in the free stream is shown to have the form of an N-wave. It is found that, on the blunted plate, the intensity of pulsations produced by weak external shock waves in boundary layer several times exceeds the intensity of pulsations produced in boundary layer on the model with a sharp leading edge.

AB - Results of an experimental study of the excitation of high-intensity disturbances by a weak external shock wave in laminar boundary layer on flat-plate models with sharp and blunted leading edges at М = 2.5 are reported. The field of disturbances produced by a 2D sticker in turbulent boundary layer on the wall of wind-tunnel test section in the free stream is shown to have the form of an N-wave. It is found that, on the blunted plate, the intensity of pulsations produced by weak external shock waves in boundary layer several times exceeds the intensity of pulsations produced in boundary layer on the model with a sharp leading edge.

KW - boundary layer

KW - experimental studies

KW - flat plate

KW - hot-wire anemometry

KW - sharp and blunt leading edges

KW - supersonic velocities

KW - wind tunnel

UR - http://www.scopus.com/inward/record.url?scp=84963760177&partnerID=8YFLogxK

U2 - 10.1134/S0869864316010054

DO - 10.1134/S0869864316010054

M3 - Article

AN - SCOPUS:84963760177

VL - 23

SP - 43

EP - 48

JO - Thermophysics and Aeromechanics

JF - Thermophysics and Aeromechanics

SN - 0869-8643

IS - 1

ER -

ID: 25840502