Paper Title
Studying the Effects of Different Inclinations given to Gurney Flap attached at Trailing Edge of a High Lift, Low Speed NACA 2412 Airfoil

Abstract
Study of L/D ratios on a high lift, low speed NACA 2412 airfoil with inclined Gurney flap attached to the trailing edge at constant angle of attack and Reynolds’s number, varying the flap inclination from 0 to higher degrees. The optimum inclination is found to be 180 from vertical where L/D coefficient is 30.6079 which is 3.34% more than L/D coefficient of flap at 00 inclination. Further inclination resulted in stalling of L/D values.