Numerical Simulation of Moving Surface Boundary-Layer Control Over Symmetric Aerofoil

The objective of the current study is to increase the lift and decrease the drag for NACA 0012 aerofoil by moving surface boundary-layer control (MSBC). The numerical simulation of lift and drag for two moving surfaces of aerofoil is carried out with commercial software “Ansys Fluent.” In the first configuration, one moving surface is considered of length 10% and other of length 15% of the chord length, both are at the upper side of the aerofoil. In the second configuration, both moving surfaces are considered of same length 10% of chord length but one is at the upper side, while other is at the lower side of the aerofoil. The results of both configurations are compared for different angle of attack and surface to free stream velocity ratio (Uc/U).