Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : November 07, 2019 - November 08, 2019
In recent years, many researchers have used a plasma actuator as novel flow control device. We provided the micro plasma actuator with electrode size of less than 1 mm. A sinusoidal micro plasma actuator induced streamwise vortex on the surface of airfoil and promoted the momentum mixing between the main flow and the boundary layer. Newly developed multi-stage plasma actuator was composed of four sinusoidal curved electrodes with rectangular and staggered arrangements. On separation suppression, PIV analysis was conducted to investigated the flow field around NACA 631-012 airfoil. It was found that the staggered multi-stage plasma actuator had a greater effect on the momentum mixing in the airfoil separation than that of rectangular arrangement. In addition, drag reduction rate measured by wind tunnel balance was higher in the staggered multi-stage curved plasma actuator.
