S0550203 Suppression of separation on an airfoil at Re = 30,000 by a pulsed DBD plasma actuator

In low Reynolds numbers region's flow, a laminar separation region and separation bubble are observed on an airfoil surface, these separation flow contribute to become worse aerodynamic characteristics of the airfoil. We intended to improve the aerodynamics of a NACA0012 airfoil using a pulsed DBD plasma actuator as a flow control device for suppressing the separated flow. We visualized and measured the flow field around the NACA0012 airfoil to examine an effect of induced flow by the plasma actuator at 30,000 of Reynolds number. As the results, we confirmed that a suppressing of separation flow were changed by flow field existing vortices on the airfoil surface which depend on F+ changing.