Design of adjustable airfoil to delay stall

In this study an alternative method is developed to reduce flow separation. Control of flow separation and transition point by means of different mechanisms such as using leading edge devices, blowing, and suction have been quite extensively researched in the literature. In this study, a new concept is investigated: Airfoil shape can be changed dynamically at different conditions (such as speed, angle of attack) also unusual airfoil design constraints can sometimes arise leading to some unconventional shapes and as a result of these desings different airfoil models can be used when the aircraft is climbing or descending. This property contribute high efficiency at any angle of attack or speed. To prove this efficiency the existing wing models (NACA 4412 and NACA 63-215) were changed to make comparisons at different angles of attack. In this study, the aerodynamic characteristics of the new wing profiles obtained by changing the x / c ratio of the two wing types (NACA 4412 and NACA 63-215) were investigated. It has been observed that the stall condition can be delayed between about 2 and 4 degrees due to the increase in maximum lift force in the wings at the end of the operation.