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• W1972503627 abstract "The modification of the tip vortex generated by a rectangular NACA 0012 wing via a tip-mounted slender half-delta wing (HDW) was attempted experimentally at Re=2.81×105. In addition to the increase in lift with increasing HDW deflection, compared to the baseline wing, the roll-up process of the tip vortex was also found to be significantly modified, as a result of the breakdown of the HDW vortex. The addition of the HDW also caused an increased total drag. Fortunately, the lift-induced drag was found to be reduced compared to its baseline counterpart for 0° and 5° HDW deflections. The change in the lift-induced drag also translates into a virtually unchanged profile drag, regardless of HDW deflection. In short, the largest lift-induced drag reduction achieved by the zero-deflection HDW resulted in an improved lift-to-drag ratio, at high angle-of-attack range, compared to the baseline wing." @default.
• W1972503627 created "2016-06-24" @default.
• W1972503627 creator A5043949186 @default.
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• W1972503627 date "2013-11-01" @default.
• W1972503627 modified "2023-09-27" @default.
• W1972503627 title "Modification of static-wing tip vortex via a slender half-delta wing" @default.
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• W1972503627 doi "https://doi.org/10.1016/j.jfluidstructs.2013.08.004" @default.
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