Experimental cross-flow control in a 3D boundary layer by multi-discharge plasma actuators

In this work, we perform experimental studies on the electrophysical and aerodynamic characteristics of two multi-discharge actuator models using near-surface dielectric barrier discharge to generate a unidirectional volumetric force impact over an extended surface area. Flow control experiments are conducted on the 3D boundary layer of a swept plate with an induced longitudinal pressure gradient using the aforementioned models in a subsonic low-turbulence wind tunnel. The results confirm the possibility of significantly decreasing the cross flow velocity in the boundary layer and stationary vortex intensity attenuation of its instability, owing to the extended volumetric force impact generated by the multi-discharge actuator system.