Flow vizualization of supersonic intake by wind tunnel. Part 1. Schlieren photograph.

Steady and quasi-steady behaviors of flows in the mixed-compression supersonic intake are visualized by using the schlieren photograph. local vapor screen method and surface oil flow method. Structures of shock wave with schlieren photograph are presented herein. Tests were done at the mach number from 1.5 to 3.0. The results show that the outline of basic flow structure affected with back pressure and air bleed effects have been proved. Especially, the visualized shock patterns of near throat regions are observed to behighly complicated, which are associated with shock boundary layer interaction.