Abstract
The experiments were carried out to observe the necessary control or elimination of the separation bubble which occurs during SWBLI (shock wave boundary layer interaction) in hypersonic flows. The dielectric barrier discharge plasma actuator (DBD-PA) as an active flow control technique has been used for this investigation. The study examines the effect of local active flow control of DBD-PA on the stability of laminar separation bubble. The Schlieren imaging is used to study the interaction between the DBD-PA and the SWBLI. The actuator was operated at pulsing frequency of 10 kHz, which generates the starting vortex at the frequency of 50 Hz. The results are presented in this paper. The actuator was arranged in two different fashions to observe its effect as a flow control mechanism in a hypersonic flow.
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