Study of Three-Dimensional Interaction Flow Fields between Swept Shock Waves and Turbulent Boundary Layers. Flow Structures and Effects of Bleed.

摘要

An experimental investigation of a three-dimensional flow field with a swept shock wave and a turbulent boundary layer interaction was in NAL's 1m X 1m Mach 4 supersonic wind tunnel. The emphasis of this study is placed on understanding the behaviors of the flow interaction with Mach number variation and the effects of bleed on the surface flow. A shock generator of 15 degree wedge placed normally on the flat plate was applied to generate an oblique shock wave. The experiments were conducted at Mach numbers of 3.25, 3.11, and 2.63. We adopted the conical coordinate system to analyze the flow. Air-bleed was also tested utilizing rows of bleed holes located at the foot print of the swept shock wave on the flat plate surface.