Vortex control by the spanwise suction flow on the upper surface of delta wing |
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Authors: | Yang Guowei Lu Xiyun Zhuang Lixian |
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Institution: | (1) Department of Modern Mechanics, University of Science and Technology of China, Hefei, 230026 Anhui, China |
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Abstract: | The numerical investigation has been performed to explore the feasibility of vortex control by leading edge sucking excitation
on a delta wing. The results reveal that the flow on the upper surface of the delta wing changes significantly in a wide range
of the angle of attack. For the vortical flow at moderate angle of attack, the secondary and tertiary vortices are weakened
or suppressed, and the total lift is almost unchanged. For the stalled flow at high angle of attack, the leading edge concentrated
vortex is recovered, and the lift is enhanced with increasing suction rate. For the bluff-body flow at even high angles of
attack, the lift can still be improved. The concentrated vortex disappears on the upper surface, and the load increment is
nearly unchanged along the chordwise direction.
The project supported by the National Natural Science Foundation of China (19802018). |
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Keywords: | vortex control separation flow delta wing numerical simulation |
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