Host: The Japan Society of Mechanical Engineers
Name : [in Japanese]
Date : September 09, 2018 - September 12, 2018
In order to investigate influence of induced flow by DBD plasma actuator on separated shear layer near separation position, we focused on flow field near leading edge of NACA0012 airfoil including the separation position. We carried out flow visualization tests on the airfoil at Reynolds number of 30,000. By results of the flow visualization, difference of driving mode of plasma actuator brings about changes of the flow field near the leading edge. In continuous mode, separated flow is changed into reattached flow on the airfoil without large vortex structure. On the other hand, in burst driving mode, reattachment flow is formed on the airfoil due to appearance of flow field involving vortexes by plasma actuator operating in all F+ conditions. The vortex's size and shedding interval are varied depending on change of F+. Changes of flow field structure near the leading edge influence on flow field of the latter part of airfoil and contribute to suppressing of the separated flow on the airfoil by using plasma actuator.
