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Nature of Wakelike and Jetlike Axial Tip Vortex Flows

机译:Wakelike和Jetlike轴向尖端涡流的性质

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摘要

The mechanisms responsible for the wakelike and jetlike axial flows of a tip vortex were investigatednexperimentally at Re u0001 3:07 u0002 105n. Both square and round tips were tested. Along the wing tip, a pocket of a higher-nthan-freestream, or jetlike, fluid was continually present, regardless of the tip condition and airfoil angle of attack u0001.nItsmaximumvelocity increased with u0001 and always exhibited a peak value around the trailing edge. In the near field,nthis jetlike fluid pocket was entrained by the shear layers and the wing wake, and it resulted in a wakelike axial flownfor smaller u0001. For higher u0001, the jetlike fluid pocket was, however, surrounded by the shear layers that, in turn,nprotected it from the destructive effects of the wing wake and remained jetlike. The switchover angle at which thenaxial flow switched from wakelike to jetlike appeared around 7 deg, regardless of the tip condition, which alsoncoincided with the angle at which the lift-to-drag ratio was a maximum. Finally, the round-tip-produced vortex wasnmore concentrated and had a higher peak tangential velocity and core circulation but a smaller core radius comparednwith those of the square tip.
机译:在Re u0001 3:07 u0002 105n上,对引起尖端涡流的尾流状和喷射状轴向流动的机理进行了研究。方形和圆形尖端均经过测试。沿机翼尖端连续存在着比自由气流高或呈喷射状的液体流体,无论尖端条件和机翼迎角u0001如何。其最大速度随u0001的增加而增加,并始终在后缘附近出现峰值。在近场,这个喷气状流体囊被剪切层和机翼尾流夹带,并导致了尾流状的轴向羽化,从而减小了u0001。对于更高的u0001,喷气状流体袋被剪切层包围,从而使它免受机翼尾流的破坏作用的影响,并保持喷气状。不论尖端条件如何,轴向流从尾流状转变为射流状的转换角都在7度左右,这也与升阻比最大的角度一致。最终,圆尖产生的涡流不再集中,并且与方形尖相比具有更高的峰值切向速度和芯环,但是芯半径更小。

著录项

  • 来源
    《Journal of Aircraft》 |2010年第6期|p.1946-1954|共9页
  • 作者

    T. Lee and J. Pereira;

  • 作者单位

    McGill University, Montreal, Quebec H3A 2K6, Canada;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

  • 入库时间 2022-08-17 23:06:12

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