Numerical study of blowing and suction control mechanism on NACA 0012 airfoil. NACA Technical Note, National Advisory Committee for Aeronautics, Washington, D.C., 1–47 (1954) Section characteristics of an NACA 0006 airfoil with area suction near the leading edge. Boundary Layer and Flow Control, Pergamon Press, Oxford, 122–143 (1961)
The history of boundary layer control research in the United States of America. Boundary Layer and Flow Control, Pergamon Press, Oxford, 104–121 (1961)įLATT, J. History of research on boundary layer control for low drag in UK. Boundary Layer Control, Pergamon Press, Oxford, 74–103 (1961) A brief history of British research on boundary layer control for high lift. In particular, it can reduce the drag by changing the vortex generation patterns. The results indicate that local vibration can improve the aerodynamic performance of the airfoil. The patterns of shear vortices caused by local vibration are also studied to determine the drag reduction mechanism of this flow control method. The optimal frequencies are near the dominant frequencies of shear layer vortices and wake vortices. The influence of oscillation frequency is investigated both by numerical simulations and experiments. The mounted position is chosen at 0.065–0.09 of chord length from the leading edge. The application parameters of local vibration on the upper surface of the airfoil are first evaluated by numerical simulations. Both wind-tunnel experiments and a large eddy simulation (LES) are carried out to study the effects of local vibration on drag reduction over a wide range of angles of attack. A flow control technique by local vibration is proposed to improve the aerodynamic performance of a typical airfoil NACA 0012.
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