Experimental Investigation of the Weak Shock Wave Influence on the Boundary Layer of a Flat Blunt Plate at the Mach Number 2.5 › Research Explorer

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

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

DOI

https://doi.org/10.1134/S0015462819020058
Final published version

Yu G. Ermolaev
A. D. Kosinov
V. L. Kocharin
N. V. Semenov
A. A. Yatskikh

Original language	English
Pages (from-to)	257-263
Number of pages	7
Journal	Fluid Dynamics
Volume	54
Issue number	2
DOIs	https://doi.org/10.1134/S0015462819020058
Publication status	Published - 1 Mar 2019

OECD FOS+WOS

Research areas

boundary layer, experiment, hot-wire anemometry, N-wave, supersonic flow, turbulence

ID: 20537697