Separation Control on NACA23012 using Synthetic Jet

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Kim, Sang Hoon; Kim, Chongam

Issue Date
American Institute of Aeronautics and Astronautics
3rd AIAA Flow Control Conference
5 - 8 June 2006, San Francisco, California
Separation control has been performed using synthetic jet on NACA23012 through
numerical approaches. To improve aerodynamic performance, synthetic jet is located near
separation point on an airfoil with leading edge and plain flap. The results of flow control
using synthetic jet shows that stall characteristics and control surface performance can be
improved substantially through the resizing of separation vortices. Stall is delayed and stall
characteristics are improved when synthetic jet is applied at the separation region of leading
edge. Also, the maximum lift is increased. Control surface effectiveness and lift are increased
when synthetic jet is applied at the leading edge of plain flap. The combination of synthetic
jet and simple high lift device is as good as fowler flap system. The results show that
aerodynamic characteristics is improved through leading edge droop with synthetic jet at
near separation point and plain flap with synthetic jet at the flap leading edge. Beside, to
obtain applicable synthetic jet velocity, we researched on multi-array synthetic jet.
Moreover, multi-location synthetic jet is simulated to remove small vortex on suction surface
of airfoil. The results show that flow around airfoil is stabilized by high frequency synthetic
jet which eliminates small vortices and attaches local flow. However, high frequency
synthetic jet changes circulation around airfoil by changing local flow velocity on airfoil
surface. It is also noted that performance of multi-array/multi-location synthetic jet is
possible to be improved by changing phase angle of multi-location synthetic jet.
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College of Engineering/Engineering Practice School (공과대학/대학원)Dept. of Mechanical Aerospace Engineering (기계항공공학부)Others_기계항공공학부
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