抄録
Recently, various studies of Micro Air Vehicle (MAV) and Unmanned Air Vehicle (UAV) have been reported from wide range points of view. The aim of this study is researching the aerodynamic improvement of delta wing in low Reynold's number region to develop an applicative these air vehicle. Various configurations of Leading Edge Flap (LEF) are used to enhance the aerodynamic characteristics in the delta wing. The fluid force measurement by six component load cell and PIV analysis are performed as the experimental method. The relations between the aerodynamical effects of the LEFs and the vortex behavior around the models are demonstrated. It is shown that the combination type LEF consisting of upward and downward deflected short span LEFs, is effectual device in the angle of attack region where lift curve slope rapidly decreases after stall.
