Study of Shock Wave and Boundary Layer Interference in Hypersonic Aerodynamics

The shock and the boundary layer of hypersonic field interference as a research key surface, the opening direct statement and closely related in the field of aerospace, and point out the characteristics of aircraft, then gradually split splicing shock concept and its principle framework of interaction with the boundary layer, flow characteristics, cause analysis to specific features all include, also by the theory of logical deduction, digital modeling analysis and laboratory validation several means respectively read again, and also clearly show, to flow change and object shape factors appearance and analysis within the scope of internal rule. After a little collation of the existing situation at home and abroad, a corner of cutting-edge achievements are also revealed. A thorough understanding of such phenomenon is of great benefit to the future technological development, and the subsequent stage still needs more progress to pave the way for the hypersonic direction.