Experimental Investigation on Shock Wave and Turbulent Boundary Layer Interactions in a Square Duct at Mach 2 and 4

In order to investigate the supersonic internal flows with shock waves, a new supersonic wind tunnel (pressure-vacuum type, Mach 2.0 and 4.0) was designed and constructed in Muroran Institute of Technology. This paper describes firstly outlines of the new Mach 4 supersonic wind tunnel, and describes secondly the location, structure and characteristics of the Mach 2 and 4 pseudo-shock waves in a square duct. The structure and characteristics of the pseudo-shock waves were clarified by color schlieren photographs and duct wall pressure measurements.