Abstract
Negative effects of shock wave – boundary layer interaction are restricting the velocity of modern commercial airplanes. Therefore, a lot of research was focused on methods of its control in the last decade. The effectiveness of passive, hybrid and active methods have been investigated and compared with one another. The main results are presented in this paper. These three methods were investigated experimentally. Static pressure distribution along the wall and the cavity were measured. At one location downstream of interaction the stagnation pressure was measured with a Pitot probe above the wall on the whole height of the λ-foot. Comparison of these results allowed us to judge the effectiveness of the method. The Schlieren system and the Mach–Zehnder interferometer were used to visualise the flow field structure.
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