![]() 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. Wonder how it did?Īlso of possible interest. Heard rumors he had the Patrol at a STOL contest recently. The 4 series has lower Reynolds #s than the 6s so don't know how it would compare side-by-side with a Cub of similar weight/power. Bob Barrows chose the Riblett GA35-413.5 for the Patrol which worked out pretty well from the reports I've read. I'm using the Riblett GA30A613.5 on my little bush plane project. I have Compufoil loaded in my computer and with it I can overlay two airfoils on top of the main airfoil. Don't see how one could go wrong with either airfoil. The Riblett GA30A613.5 should be just a tad bit better. The USA35B is a good airfoil, no question about it. I've read and utilized both and Riblett has his stuff wired. and it's a lot easier read than Abbott and Von Doenhoff's book: The Theory of Wing Sections. The EAA sells a book (about $20) called GA Airfoils written by Harry Riblett which is a very informative book that the average aviator should have no problem understanding.
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