複数の前縁フラップの組合せによるデルタ翼空力特性の改善

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 to research the aerodynamic improvement of delta wing in low Reynolds number region to develop an applicative these air vehicles. As an attractive tool in delta wing, leading edge flap (LEF) is employed to directly modify the strength and structure of vortices originating from the separation point along the leading edge. Various configurations of LEF such as drooping apex flap and upward deflected flap are used in combination to enhance the aerodynamic characteristics in the delta wing. In this study, the numerical simulations are performed based on the model in which different shaped leading edge flaps are assembled in the delta wing at various mounting angle. Additionally, the fluid force measurement by six component load cell and PIV analysis are performed in the wind tunnel experiments. The relations between the aerodynamic superiority and the vortex behavior around the models are clarified.