The airfoil is prone to flow separation under low Reynolds number flow conditions, which leads to a sharp deterioration of aerodynamic performance of micro aircraft. This paper proposes a bionic separation flow airfoil design concept, which turns to fix the separation point through the leading edge sharpening structure and induce stable vortices, combined with the rear edge arc airfoil surface to promote flow reattachment and vortex stability. Numerical simulation results show that This bionic airfoil can effectively suppress flow separation over a wide Angle of attack (8°-16°), significantly increase lift coefficient, significantly improve stall characteristics, and extend the efficient operating range by about twice compared to traditional airfoils. Parameter analysis reveals the influence of key geometric parameters such as the leading edge tip Angle and the installation position of the arc wing on aerodynamic performance.