Abstract
In this study, we investigated the effects of surface sliding discharge of a dielectric barrier discharge (SL-DBD) plasma actuator on the boundary layer flow using the time-resolved particle image velocimetry (PIV) technique. According to the PIV measurements, the peak-shaped mean jet flow is induced by the SL-DBD plasma actuator in quiescent air. Under the freestream of U∞ = 6 m/s on the flat plate, the results show that the streamwise velocity fluctuation induced by SL-DBD plasma is increased pronouncedly at the downstream of the actuator. Meanwhile, the mean flow velocity increases obviously in the downstream of the actuator. The instantaneous results show the formation of the vorticity at the bottom of the boundary layer after the plasma excitation. In addition, the vorticity has the behavior to lift up, possibly because of the induced peak-shaped jet.
Highlights
Surface dielectric barrier discharge (DBD) plasma actuators have advantages of being entirely surface mounted, with no moving parts, fast response time, and low power consumption
The induced flow field of the sliding discharge DBD (SL-DBD) actuator in quiescent air is first investigated by the particle image velocimetry (PIV) measurement
The jet induced by the AC-DBD actuator is tangent to the wall,5 while the jet induced by the SL-DBD actuator is a little different
Summary
Surface dielectric barrier discharge (DBD) plasma actuators have advantages of being entirely surface mounted, with no moving parts, fast response time, and low power consumption. Roupassov et al. presented a review of data on controlling the boundary layer attachment by a high-voltage pulsed-periodic nanosecond plasma excitation. The results showed that under the conditions of the simulated experiments, fast gas heating takes place in the boundary layer, leading to the generation of a “micro” shock wave. Zheng and Zhao presented the shock wave behavior generated from a single shot of the NS-DBD plasma actuator with varying pulse voltages in quiescent air was studied by experiments and numerical simulations.. The DBD plasma driven by nanosecond pulse was used to control the flow separation in the leading edge of the NACA 0015 wing at different post stall angles of attack to extend the stall angle at low Reynolds numbers by functioning as an active trip by Retheml et al.. We further explore the effects of the SL-DBD actuator on the boundary layer flow using the time-resolved particle image velocimetry (PIV) technique
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