DBD-PAによる翼前縁付近での誘起流の変化が剥離抑制に与える効果

抄録

In order to suppress separated flow by turbulent transition in initial region of the separated shear layer, we introduced induced flow opposite to uniform flow by using plasma actuator. We carried out flow visualization tests on a NACA0012 airfoil at Reynolds number of 30,000. By results of the flow visualization, in continuous mode, the separated flow could not be suppressed and flow field make separated flow encouragement. In addition, by changing of applied voltage, changing of induced flow velocity influenced on flow state near separation position. On the other hand, in burst driving mode, in inverse direction of induced flow, flow field with vortex structure was confirmed on wing surface like flow field of forward direction. Therefore, it is considered that the separated flow can be suppressed by injecting the induced flow by operating plasma actuator in inverse direction in burst driving mode.