REATTACHMENT 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 corner for the Mach number of the incident flow M = 6 and 8. The shock-wave structure of the flow in its reattachment 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.