A study on the improvement of the wing performance by using sinusoidal leading edge

(Investigation of the effectiveness range of sinusoidal leading edge)

Abstract

In this study, we focused on the wing with sinusoidal leading edge (SLE) to control flow separation at low Reynolds Number. In previous study, it was found that the effectiveness of SLE on wing performance changes depending on the wing cross section and angle of attack. So, in this study, we predicted the effective region of SLE in advance. From the results of wind tunnel experiments and numerical simulations, we found that the boundary profile between separation and unseparation region. By using the boundary profile, we could predict the effective region of SLE in advance even if the maximum wing camber changes.