![]() ![]() ![]() YUAN, W., XU, H., KHALID, M., and RADESPIEL, R. Flow control by spanwise blowing on a NACA 0012. An Introduction to Computational Fluid Dynamics: the Finite Volume Method, 2nd ed., Pearson Education, London, 40–113 (2007) NASA Technical Memorandum, National Aeronautics and Space Administration, Hampton, Virginia, 1–27 (1996) Computer program to obtain ordinates for NACA airfoils. Vortex shedding of an airfoil at low Reynolds numbers. Coherent structures in an airfoil boundary layer and wake at low Reynolds numbers. On vortex shedding from an airfoil in low-Reynolds-number flows. Low-Reynolds-number separation on an airfoil. Progress in Aerospace Sciences, 5, 71–103 (1964) Low-speed flows involving bubble separations. ![]() Airfoil performance at low Reynolds numbers in the presence of periodic disturbances. Aerodynamic analysis of a localized flexible airfoil at low Reynolds numbers. Journal of Fluids and Structures, 46, 42–58 (2014) Computation of unsteady viscous flow around a locally flexible airfoil at low Reynolds number. Flow separation control with microflexural wall vibrations. High-incidence airfoil aerodynamics improvement by leading-edge oscillating flap. Use of piezoelectric actuators for airfoil separation control. SEIFERT, A., ELIAHU, S., GREENBLATT, D., and WYGNANSKI, I. Delay of airfoil stall by periodic excitation. SEIFERT, A., DARABI, A., and WYGANSKI, I. Dynamics of airfoil separation control using zero-net mass-flux forcing. Science in China Series E: Technological Sciences, 51(9), 1315–1344 (2008) Review of zero-net-mass-flux jet and its application in separation flow control. Aerodynamic flow control over an unconventional airfoil using synthetic jet actuators. Numerical investigation of synthetic-jet flow fields. Journal of the American Helicopter Society, 43(4), 303–311 (1998) Effects of zero-mass “synthetic” jets on the aerodynamics of the NACA-0012 airfoil. 35th AIAA Fluid Dynamics Conference and Exhibit, American Institute of Aeronautics and Astronautics, Toronto, 4633–4644 (2005) Numerical simulations of plasma based flow control applications. Separation control using plasma actuators: dynamic stall vortex control on oscillating airfoil. 44th AIAA Aerospace Sciences Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Reno, Nevada, 1208–1221 (2006) 43rd AIAA Aerospace Sciences Meeting and Exhibit, American Institute of Aeronautics and Astronautics, Reno, Nevada, 578–563 (2005)ĬORKE, T. Overview of plasma flow control: concepts, optimization, and applications. 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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