by

The interaction of a concentrated vortex with a shock wave may occur in many instances in the operational environment of supersonic aircraft and missiles. The interaction may be the result of vortices created by the forward components of a supersonic vehicle convecting downstream and interacting, for example, with shock waves present in front of air intakes or other wings. The objective of the present work was to conduct an experimental study simulating the interaction of streamwise wing-tip vortices with normal shock waves in a Mach 3 flow. Therefore, an experimental study was conducted to simulate the interaction of streamwise wing-tip vortices and normal shock waves (fig.1). In this paper two recently developed visualization techniques are shown. The results of the Background Oriented Scattering (BOS), invented at DLR, are compared to the flow-field visualizations, obtained by using the ISL holographic filters. To elucidate the complex flow containing shock waves, backflow and large-scale fluctuations, measurements using a laser Doppler velocimeter (LDV) were carried out (fig.2)