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, Russian Academy of Sciences, Novosibirsk, 630090, Russia
Keywords: угол сжатия, сверхзвуковое течение, скачки уплотнения, ламинарный отрыв, высоконапорный слой, compression angle, supersonic flow, shock waves, laminar separation, high-pressure layer
Abstract
This paper describes a study of a laminar separated flow in a compression angle for the Mach number of the incident flow M = 6; 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.
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