Active Shock Control in a Transonic Flow

The control authority of fluidic actuation on a transonic shock and the induced adjacent separated flow domain are characterized over a two-dimensional convex surface in wind tunnel experiments. The shock is manipulated indirectly by controlling the induced separated flow downstream. Actuation is applied using a spanwise array of small-scale, high-frequency (nominally 10 kHz) fluidic oscillating jets that effect separation delay by enhancing small-scale mixing within the separating shear layer. This actuation approach enables control of both the shock position and suppression of its unsteady oscillation. The effects of the actuation amplitude are assessed using measurements of the static and dynamic surface pressure and PIV measurements. In addition, the correlation between the shock displacement and surface pressure are explored for application of closed-loop control of the shock.

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