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This article is cited in 1 scientific paper (total in 1 paper)
Attachment of a laminar separated flow at a hypersonic velocity of the flow
V. I. Zapryagaev, I. N. Kavun, L. P. Trubitsyna Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch of the Russian Academy of Sciences, 630090, Novosibirsk, Russia
Abstract:
This paper describes a study of a laminar separated flow in a compression angle for the Mach number of the incident flow $\mathrm{M}=6$ and $8$. The shock-wave structure of the flow in an attachment region is considered. The formation mechanism of a high-pressure layer, which is a narrow gas region located above the boundary layer downstream from the attachment line, is investigated.
Keywords:
compression angle, supersonic flow, shock waves, laminar separation, high-pressure layer.
Received: 29.05.2020 Revised: 29.05.2020 Accepted: 29.06.2020
Citation:
V. I. Zapryagaev, I. N. Kavun, L. P. Trubitsyna, “Attachment of a laminar separated flow at a hypersonic velocity of the flow”, Prikl. Mekh. Tekh. Fiz., 61:5 (2020), 32–39; J. Appl. Mech. Tech. Phys., 61:5 (2020), 710–716
Linking options:
https://www.mathnet.ru/eng/pmtf267 https://www.mathnet.ru/eng/pmtf/v61/i5/p32
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Abstract page: | 44 | Full-text PDF : | 3 | First page: | 8 |
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