In this research, the winglet attached to the NACA0012 airfoil is studied through wind tunnel experiments to analyze its aerodynamic characteristics with respect to the cant angle and incidence angle which are key design factors of the winglet. Additionally, split scimitar winglet's characteristics are verified. Results show that the winglet model with a larger cant angle has a larger lift-to-drag ratio and a smaller size of pitching moment coefficient. The model with an incidence angle of 0 degree shows improvements of aerodynamic characteristics at the range of low angle of attack and one with an incidence angle of -4 degree does at the range of high angle of attack. The split scimitar winglet model has a larger lift-to-drag ratio and a smaller size of pitching moment coefficient than the reference of winglet model.