The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge

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The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge. / Kocharin, V. L.; Kosinov, A. D.; Yatskikh, A. A. et al.

In: Thermophysics and Aeromechanics, Vol. 26, No. 6, 01.11.2019, p. 803-809.

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

BibTeX

@article{2e2a7c04f71845e7ada67f0615ec03ac,

title = "The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge",

abstract = "The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred.",

keywords = "leading blunt edge, longitudinal vortex, N-wave, supersonic boundary layer, swept plate, COUPLE, MACH WAVE, LAMINAR-TURBULENT TRANSITION",

author = "Kocharin, {V. L.} and Kosinov, {A. D.} and Yatskikh, {A. A.} and Ermolaev, {Yu G.} and Semionov, {N. V.} and Piterimova, {M. V.} and Shevelkov, {S. G.} and Minin, {O. P.}",

note = "Publisher Copyright: {\textcopyright} 2019, V.L. Kocharin, A.D. Kosinov, A.A. Yatskikh, Yu.G. Ermolaev, N.V. Semionov, M.V. Piterimova, S.G. Shevelkov, and O.P. Minin. Copyright: Copyright 2020 Elsevier B.V., All rights reserved.",

year = "2019",

month = nov,

day = "1",

doi = "10.1134/S0869864319060027",

language = "English",

volume = "26",

pages = "803--809",

journal = "Thermophysics and Aeromechanics",

issn = "0869-8643",

publisher = "PLEIADES PUBLISHING INC",

number = "6",

}

RIS

TY - JOUR

T1 - The impact of weak shock waves on the flow in the boundary layer of a flat plate with a variable sweep angle of the leading edge

AU - Kocharin, V. L.

AU - Kosinov, A. D.

AU - Yatskikh, A. A.

AU - Ermolaev, Yu G.

AU - Semionov, N. V.

AU - Piterimova, M. V.

AU - Shevelkov, S. G.

AU - Minin, O. P.

N1 - Publisher Copyright: © 2019, V.L. Kocharin, A.D. Kosinov, A.A. Yatskikh, Yu.G. Ermolaev, N.V. Semionov, M.V. Piterimova, S.G. Shevelkov, and O.P. Minin. Copyright: Copyright 2020 Elsevier B.V., All rights reserved.

PY - 2019/11/1

Y1 - 2019/11/1

N2 - The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred.

AB - The impact of weak shock waves on the boundary-layer flow of a flat blunt plate installed along the stream was experimentally studied for different sweep angles of the leading edge of the plate at Mach number 2. The shock waves in the incoming flow in the form of an N-wave were generated by 150×7×0.13-mm two-dimensional roughness provided on the side wall of the T-325 wind tunnel. It was confirmed that, when an N-wave was incident onto the plate leading edge with zero sweep angle, generation of longitudinal vortices accompanied by an increase in the pulsation level and by a change in the spectral composition of perturbations, was observed in the boundary layer. Anemometric data showed that, when the sweep angle of the leading edge changed from 0 to 25 degrees under the impact of the “catching-up” incident weak shock wave, the widening of the vortex in the supersonic boundary layer occurred.

KW - leading blunt edge

KW - longitudinal vortex

KW - N-wave

KW - supersonic boundary layer

KW - swept plate

KW - COUPLE

KW - MACH WAVE

KW - LAMINAR-TURBULENT TRANSITION

UR - http://www.scopus.com/inward/record.url?scp=85080131407&partnerID=8YFLogxK

U2 - 10.1134/S0869864319060027

DO - 10.1134/S0869864319060027

M3 - Article

AN - SCOPUS:85080131407

VL - 26

SP - 803

EP - 809

JO - Thermophysics and Aeromechanics

JF - Thermophysics and Aeromechanics

SN - 0869-8643

IS - 6

ER -

ID: 23666009