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ACTIVE SEPARATION CONTROL ON A SLATLESS 2D HIGH-LIFT WING SECTION

机译：无节距二维高升机翼部分的主动分离控制

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摘要

In the present paper, active separation control byrnmeans of pulsed blowing from the flap shoulder in orderrnto delay turbulent flow separation is investigated.rnExperiments are carried out on a two-dimensionalrnhigh-lift configuration consisting of a main elementrnand a single slotted flap for a Reynolds number ofrnabout Rec = 1u0001106. The trailing edge flap is equippedrnwith a specially designed excitation mechanism that isrncapable of producing a pulsed wall jet with high jetrnvelocities. Compressed air and fast switching solenoidrnvalves are used to excite the flow at different locations.rnThe direction of the pulsed jet is also variedrnfor the measurements. Furthermore, the effect of flaprngap and flap overlap on excitation location sensitivityrnis investigated. The results include measurementsrnfrom a six- component wind tunnel balance and miniaturernpressure sensors. For selected configurations enhancementsrnin lift coefficients of up to 25% are possible,rnwhile the drag forces are reduced.
机译：本文研究了从襟翼肩部以脉冲吹动的主动分离控制方法，以按顺序延迟湍流分离。rn在二维高升构型上进行了实验，该构型由主要元素和单个开槽襟翼组成，用于雷诺数Recn = 1u0001106。后缘襟翼配备有专门设计的激励机构，该激励机构不能产生具有高射流速度的脉冲壁射流。压缩空气和快速切换电磁阀用于激发不同位置的流量。用于测量的脉冲射流方向也有所变化。此外，研究了拍打和拍打重叠对激励位置灵敏度的影响。结果包括六分量风洞天平和微型压力传感器的测量值。对于选定的配置，可以将提升系数提高25％，同时减小阻力。

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  • 会议地点 Manchester(GB)
  • 作者

    F. Haucke; I. Peltzer; W. Nitsche;

  • 作者单位

    Chair for Aerodynamics, Department of Aeronautics and Astronautics Berlin Institute of Technology, Marchstr.12, 10587 Berlin, Germany Email: frank.haucke@ilr.tu-berlin.de;

    Chair for Aerodynamics, Department of Aeronautics and Astronautics Berlin Institute of Technology, Marchstr.12, 10587 Berlin, Germany Email: inken.peltzer@tu-berlin.de;

    Chair for Aerodynamics, Department of Aeronautics and Astronautics Berlin Institute of Technology, Marchstr.12, 10587 Berlin, Germany;

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  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空、航天技术的研究与探索;
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