Study of 2-D Shock-Wave / turbulent Boundary Layer Interaction

Abstract

Shock-Wave / turbulent Boundary Layer interactions (SWTBLI) play an important role in optimizations of supersonic and hypersonic inlets. For 50 years SWTBLI's have been experimentally and numerically studied, but the mechanisms which lead to the unsteady motion of the separation bubble are still not fully understood. This paper presents experimental results of a nominally 2D impinging shock wave interaction with the turbulent boundary layer developing on a at plate at Mach 3. The experiments were carried out in the Ludwieg Tube Facility at DLR Göttingen, employing high-speed shadowgraphy, quantitative infrared thermography, oil film interferometry, as well as static and dynamic wall pressure measurements. In order to analyze different shock strengths and turbulent boundary layer conditions the location of the impinging shock and the diameter of the cylindrical shock generator were varied. A comprehensive data set was built to conduct scaling analysis and CFD validations.