抄録
Characteristics of a flow field around a wing with surface oscillation are investigated using an immersed boundary method. The immersed boundary method is to represent the effect of an immersed body in a flow by a virtual volume force. In this study, the method is successfully adapted to an unstructured-grid solver "FrontFlow/red" based on the Finite Volume scheme. Low Reynolds number flows, such as flows around Micro Aerial Vehicles and Unmanned Aerial Vehicles, are likely to cause early separation. A possible way to restrict this separation is to apply an oscillatory morphing wing shape. Comparisons between static and actuated simulations indicate that the actuation does significantly reduce separation for low Reynolds number cases.
