Abstract
Unsteady transonic shock boundary layer interaction on two-dimensional symmetrical lifting airfoils at constant free-stream conditions were recently described in Ref. 1. The literature survey given therein shows, that unsteady flow behaviour is mainly initiated by a separated boundary layer. Although the interaction phenomena are not fully understood, four physically possible mechanisms have been proposed to explain the wave pattern. In this paper experiments will be described which are aimed at finding out how shock oscillations on lifting airfoils in transonic flow can be prevented. Then the unsteady transonic flow about a thick biconvex circular-arc airfoil will be discussed in the frame of new experimental results. The intense shock oscillations observed in experiments will be explained by two mechanisms, one of which shows some similarities to the transonic aileron buzz. Therefore a comparison with the theoretical results of Eckhaus (Refs. 2 and 3) will be made. Finally it is demonstrated how shock oscillations can be suppressed by different techniques as for example by suction or tangential blowing. The shock oscillations were studied with several optical methods which together with other techniques were described in Ref. 1.
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