23rd Congress of International Council of the Aeronautical Sciences, 8-13 September, 2002, Toronto, Canada
Paper ICAS 2002-R24

EXPERIMENTAL STUDY OF TURBULENT WAKE FLOW DEVELOPMENT BEHIND A FINITE WING WITH HIGH ANGLE OF ATTACKS

F. B. Hsiao (1), C-Z. Cheng (1), W-J. Liu (1), C-C. Hsu (2)
(1) National Cheng Kung University, Taiwan; (2) Air Force Aeronautic Technique School, Kaohsiung, Taiwan

Keywords: trailing vortex, wake flow, downwash

The experimental approaches are employed to investigate the wake development of finite wing with aspect ratio 3 by hot-wire anemometry. Results indicated that the wake of the finite wing in the near field can be divided into two parts in the span-wise direction: one is with the same behavior as of the 2-D wake and the other is affected by the wing-tip vortex. In comparison with the downwash rates of the theoretical analysis, a good consistence can be obtained. The similarity distribution of mean velocity and root-mean-square velocity can also be observed in the region. In the 3-D region, the low pressure region will form as the result of the development of the wing tip vortices to the downstream. According to the downstream evolution of the U contours, the development of trailing vortices can be further characterized into three different processes.

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