Study of a Shock Wave Turbulent Boundary Layer Interaction by Means of Optical Methods

The velocity and temperature fields of an incident shock wave boundary layer interaction region for a flat plate flow is investigated. The research was carried out on a supersonic wind tunnel of periodic action with a closed working part and an adjustable supersonic nozzle, and impulse shock tube with flow duration up to several milliseconds. The shock system was generated by a wedge mounted at a distance of 20 mm from the upper wall, and by local inhomogeneities of the channel. The thickness of the boundary layer at the beginning of the test section on the upper and lower walls was about 6 mm. Experimental channels are equipped with optical quartz side windows and transparent upper and lower plexiglass sections, which allows the use of panoramic visualization methods. The distribution of the longitudinal and transverse components of the flow velocity in the interaction region of the incident shock wave with a flat plate was determined using the PIV method. The flow pattern in the area of interaction of the incident shock wave with the wall was also visualized using infrared thermography and the IAB-451 shadow device.