Attachment of a laminar separated flow at a hypersonic velocity of the flow

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.