Boundary-Layer Transition Control by Plasma Crossflow Reduction in Swept Wing

The boundary-layer transition caused by the crossflow instability in a swept wing is controlled by a plasma actuator (PA). In this study, the control concept is to suppress the crossflow generated at leading edge of the wing by using PAs. The PAs are installed at the leading edge so that the body force can be applied in the direction that cancels the crossflow. An attempt was made to delay the boundary-layer transition by driving a PA. In a wind tunnel experiment, we investigate the transition position and velocity in the boundary layer at U = 20 m/s. The experimental results showed that the transition position delayed when PA was driven. From the spectral analysis of the velocity in the boundary layer, we found that the boundary-layer transition process changed from crossflow instability mode when PA was driven.