The effects of leading edge modifications on the stalling characteristics of an NACA 0015 panel wing model were investigated in a series of low speed wind tunnel tests. The modification typically consisted of adding a 14% Clark Y glove onto a portion of the leading edge. Six-component balance data, pressure distribution measurements and oil flow visualization tests were completed at a Reynolds number based on chord of 2.0 x 10^6 for increasing and decreasing angles of attack from 0° to 50°. The leading edge modifications produce stabilizing vortices at stall and beyond. These vortices have the effect of fixing the stall pattern of the wing such that various portions of the wing upper surface stall nearly symmetrically. This results in a higher lift on the modified wing as compared to the lift on the unmodified wing in the post-stall region. The lift curve slope of the modified and unmodified wings remained essentially constant at 0.071 per degree. Two lift-coefficient peaks were obtained for the baseline NACA 0015 wing at angles of attack of 17° and 30°. The twin-peak behavior of the lift curve was also observed on the modified wings. The drag coefficient obtained with several modified configurations was smaller than the drag coefficient of the baseline NACA 0015 wing in the pre-stall region. Also a smaller center of pressure shift with angle of attack was observed with several modified configurations. Considering a smoother variation of lift, pitching moment, rolling moment at stall and a smaller drag and center of pressure movement to be desired criteria, the best configuration tested consisted of placing the glove on the entire leading edge except for a gap at 25% to 50% of the semispan.