Abstract
The structures of a flow field induced by a plasma actuator were investigated experimentally in quiescent air using high-speed Particle Image Velocimetry (PIV) technology. The motivation behind was to figure out the flow control mechanism of the plasma technique. A symmetrical Dielectric Barrier Discharge (DBD) plasma actuator was mounted on the suction side of the SC (2)-0714 supercritical airfoil. The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of [Formula: see text] = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV. The high speed PIV measurement of the induced airflow suggested that the plasma actuator could excite the flow instabilities which lead to production of the roll-up vortex. Analysis of transient results indicated that the roll-up vortices had the process of formation, movement, merging and breakdown. This could promote the entrainment effect of plasma actuator between the outside airflow and boundary layer flow, which is very important for flow control applications.
Highlights
Flow control using Dielectric Barrier Discharge (DBD) plasma actuator is a booming field of investigation
The results demonstrated that the plasma jet had some coherent structures in the separated shear layer and these structures were linked to a dominant frequency of f0 = 39 Hz when the peak-to-peak voltage of plasma actuator was 9.8 kV
The flow field induced by a symmetrical DBD plasma actuator which is mounted on the suction side of the SC (2)-0714 supercritical in quiescent air has been investigated using high-speed Particle Image Velocimetry (PIV) technology
Summary
Flow control using Dielectric Barrier Discharge (DBD) plasma actuator is a booming field of investigation. When the two electrodes are connected to a high-voltage, high-frequency AC power supply, the air around the exposed electrode is ionized, producing a body force that acts on the surrounding air. This induces a wall jet on the edge of the exposed electrode. As a flow control method, the plasma actuators have been studied on various aerodynamic research objects in wind tunnel, such as airfoil,[14,15,16] wing,[17,18,19,20] cylinder,[21,22,23,24] turbines blade,[25] and compressor cascade.[26,27]
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
