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The surface-flow characteristics and aerodynamic performance of a cantilever wing model subjected to the influence of a leading-edge control rod are studied in a wind tunnel. Circular rods of various materials and diameters installed at various distances from the leading edge of the wing are tested at low chord Reynolds numbers. Some selected small-diameter rods present a self-excited transverse vibration when they are placed very close to the leading edge. Through the surface oil-flow technique, the natural wing displays complex surface-flow patterns, which are commonly observed at a Reynolds-number range of 10 4 -10 6 . Under the action of rod vibration, turbulent boundary-layer behaviors usually found on a wing surface at large Reynolds numbers are observed. The separation resistance of boundary layer on the vibrating-rod controlled wing is remarkably larger than the natural and rod-wake disturbed wings
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Huang et al. (2002) studied this question.
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