In order to upsurge the maneuverability of micro aerial vehicles, sinusoidal leading edge inspired from the whale flipper was applied as a passive stall control method. Although this method could be useful to control stall phenomena but effect of geometrical properties on the flow physic must be investigated to reach the root of these effects. According to preceding researches, not much attention has been paid to the effects of some parameters on the sinusoidal leading-edge wing in the post-stall region. In this study, the variation of sectional airfoil characteristics and wavelength and Amplitude of sinusoidal leading edge shape has been examined at post-stall angle to better understanding the flow behavior and distribution around the full-span wing. Therefore, the airfoils’ cross section considered as EPPLER with a wavy leading edge. The results showed that by decreasing the wavelength, the lift coefficient and the drag coefficient decreased by 19% and 15%, respectively. On the other hand, by reducing the Amplitude, it would be obvious an increase in the lift coefficient of about 0.7%, instead a reduction in the drag coefficient of about 7%. Also as the thickness and camber increasing, the lift to drag ratio goes down by about 2.41% and 1.06%, respectively. Finally by rising the last design variable (maximum proximity), the lift to drag ratio decrease about 11.3%.

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