Standard

Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5. / Ermolaev, Yu G.; Kosinov, A. D.; Kocharin, V. L. et al.

In: Fluid Dynamics, Vol. 54, No. 2, 01.03.2019, p. 257-263.

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

Harvard

Ermolaev, YG, Kosinov, AD, Kocharin, VL, Semenov, NV & Yatskikh, AA 2019, 'Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5', Fluid Dynamics, vol. 54, no. 2, pp. 257-263. https://doi.org/10.1134/S0015462819020058

APA

Ermolaev, Y. G., Kosinov, A. D., Kocharin, V. L., Semenov, N. V., & Yatskikh, A. A. (2019). Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5. Fluid Dynamics, 54(2), 257-263. https://doi.org/10.1134/S0015462819020058

Vancouver

Ermolaev YG, Kosinov AD, Kocharin VL, Semenov NV, Yatskikh AA. Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5. Fluid Dynamics. 2019 Mar 1;54(2):257-263. doi: 10.1134/S0015462819020058

Author

Ermolaev, Yu G. ; Kosinov, A. D. ; Kocharin, V. L. et al. / Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5. In: Fluid Dynamics. 2019 ; Vol. 54, No. 2. pp. 257-263.

BibTeX

@article{a9ea49e4d8aa4f53979fc02f77033988,
title = "Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5",
abstract = "The generation of two weak shock waves by a two-dimensional roughness mounted on the side wall of the test section of a wind tunnel and their influence on the supersonic boundary layer of a flat blunt plate is experimentally investigated at the Mach number 2.5. The measurements are made using a constant temperature hot-wire anemometer. In the boundary layer of the plate the profiles of the mean mass flow rate and the r.m.s. fluctuations are measured in the region of streamwise vortices generated by the pairwise weak shock wave upon the interaction with the flow in the vicinity of the leading edge of the model. High-intensity fluctuations generated by the influence of the weak shock wave are found to exist.",
keywords = "boundary layer, experiment, hot-wire anemometry, N-wave, supersonic flow, turbulence",
author = "Ermolaev, {Yu G.} and Kosinov, {A. D.} and Kocharin, {V. L.} and Semenov, {N. V.} and Yatskikh, {A. A.}",
year = "2019",
month = mar,
day = "1",
doi = "10.1134/S0015462819020058",
language = "English",
volume = "54",
pages = "257--263",
journal = "Fluid Dynamics",
issn = "0015-4628",
publisher = "Maik Nauka-Interperiodica Publishing",
number = "2",

}

RIS

TY - JOUR

T1 - Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5

AU - Ermolaev, Yu G.

AU - Kosinov, A. D.

AU - Kocharin, V. L.

AU - Semenov, N. V.

AU - Yatskikh, A. A.

PY - 2019/3/1

Y1 - 2019/3/1

N2 - The generation of two weak shock waves by a two-dimensional roughness mounted on the side wall of the test section of a wind tunnel and their influence on the supersonic boundary layer of a flat blunt plate is experimentally investigated at the Mach number 2.5. The measurements are made using a constant temperature hot-wire anemometer. In the boundary layer of the plate the profiles of the mean mass flow rate and the r.m.s. fluctuations are measured in the region of streamwise vortices generated by the pairwise weak shock wave upon the interaction with the flow in the vicinity of the leading edge of the model. High-intensity fluctuations generated by the influence of the weak shock wave are found to exist.

AB - The generation of two weak shock waves by a two-dimensional roughness mounted on the side wall of the test section of a wind tunnel and their influence on the supersonic boundary layer of a flat blunt plate is experimentally investigated at the Mach number 2.5. The measurements are made using a constant temperature hot-wire anemometer. In the boundary layer of the plate the profiles of the mean mass flow rate and the r.m.s. fluctuations are measured in the region of streamwise vortices generated by the pairwise weak shock wave upon the interaction with the flow in the vicinity of the leading edge of the model. High-intensity fluctuations generated by the influence of the weak shock wave are found to exist.

KW - boundary layer

KW - experiment

KW - hot-wire anemometry

KW - N-wave

KW - supersonic flow

KW - turbulence

UR - http://www.scopus.com/inward/record.url?scp=85066797610&partnerID=8YFLogxK

U2 - 10.1134/S0015462819020058

DO - 10.1134/S0015462819020058

M3 - Article

AN - SCOPUS:85066797610

VL - 54

SP - 257

EP - 263

JO - Fluid Dynamics

JF - Fluid Dynamics

SN - 0015-4628

IS - 2

ER -

ID: 20537697