Numerical Analysis of Effects of Leading-Edge Protuberances on Aircraft Wing Performance

Abstract

The effects of biologically inspired leading-edge protuberances on aircraft wings were investigated by using a numerical scheme. Simulations were performed at a Reynolds number of 5.7 x 10(5) on wings with leading-edge sinusoidal protuberances and baseline configuration. All wings had the same cross section of NACA 2412. In all cases of the modified wings, a decrease in lift and an increase in drag at low angles of attack were observed. However, at high angles of attack (alpha >= 16 deg), the lift of the modified wings was up to 48% greater than that of the baseline wing, with 40% less drag or no drag penalty. The amplitude of protuberances significantly affects wing performance. Although the maximum lift generated by modified wings was lower than baseline, protuberances along the leading edge of the wing proved to have a profound advantage in obtaining higher lift at high angles of attack.