Stall Delay Characteristics Study of NACA 2412 Wing with Outward Dimples

Flow separation in an aircraft is one of the ground causes of decrease in the lift and increase in the pressure drag which eventually leads to loss of energy, vibrations in machinery and may cause structural failure of the aircraft. Many studies and research works have been carried out on delaying boundary layer separation. One of such works is the implementation of various active and passive devices on the surface of the wing. In this research work, we have used one such device called a passive dimple. By placing these dimples on the upper surface of the wing, a turbulent flow is induced which produces vortices, causing the boundary layer to stay attached to the surface of the wing to some extent and thereby increasing the stall angle of the aircraft. In this research work, we have placed outward dimples on the upper surface of the wing at various positions and ran simulations at different angle of attacks to observe the effects.