Numerical investigation on boundary layer control through moving surface in NACA 0012 airfoil Available to Purchase

This study focuses on the drag reduction by reducing adverse pressure gradient and delaying the flow separation of 2D NACA 0012 airfoil by moving surface through numerical simulation. Two particular cases are considered here. When ‘single moving surface’ is considered, only one moving surface of 10% of the chord length(c) is placed at upper surface of the airfoil starting from 0.05c to 0.15c. When ‘double moving surface’ is considered, one moving surface of 10% of the chord length is placed at upper surface starting from 0.05c to 0.15c and one moving surface of same size is placed at lower surface from 0.05c to 0.15c. Momentum injection into the flow field moves the separation of boundary layer in the vicinity of trailing edge of the airfoil. By momentum injection through single moving surface with the surface velocity twice the free stream velocity and for different angle of attack it is possible to reduce the average drag coefficient by 23.9%. And for same condition with double moving surface it is possible to reduce the average drag coefficient by 25.9%. For moving surface boundary condition, boundary-layer separation is delayed along the chord length on the upper surface of the airfoil.