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首页> 外文期刊>Journal of Aircraft >Separation Control on a Trailing-Edge Flap Using Air Jet Vortex Generators
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Separation Control on a Trailing-Edge Flap Using Air Jet Vortex Generators

机译：使用喷气涡流发生器的后缘襟翼分离控制

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摘要

This paper has outlined the design requirements for civil-transport high-lift systems and made a case that value could be increased by the use of flow control to allow relaxation of the high-lift system positional tolerances without loss in overall performance. Experimental work using a swept panel high-lift model has identified that relaxation of the flap gap from 2.5 to 3.5%c at a flap deflection of 37.5 deg led to an approximately 0.2 drop in C_L over the useful angle range of the high-lift system. Surface flow-visualization studies have shown that this loss in performance caused by separation of the flap upper-surface boundary layer. The application of flow control in the form of AJVGs approximately 30% x/c from the leading edge of the flap running at a C_V of 2.6 enabled reattachment of the flap upper-surface boundary layer and hence recovery of the original flap performance. Experiments at increased flap deflection demonstrated that the performance boundaries defined by the proposed flow control model are valid. Investigation of the effect of actuator spacing showed that a hole spacing ratio of 20 gave the best system gain. At experimental scale, results collapse reasonably well with speed using C_V or C_μ as the similarity parameter. Provisional scaling of the experimental results to an A320 type aircraft indicate that approximately 0.5% of engine landing mass flow would be required based on a velocity ratio scaling and 8% based on momentum ratio scaling.
机译：本文概述了民用运输高举系统的设计要求，并提出了可以通过使用流量控制来增加价值的情况，以允许放宽高举系统的位置公差而不会损失整体性能。使用后掠式高升力模型的实验工作已确认，在高升力系统的可用角度范围内，当襟翼偏转37.5度时，襟翼间隙从2.5％c松弛到3.5％c，导致C_L下降约0.2 。表面流可视化研究表明，这种性能损失是由襟翼上表面边界层的分离引起的。从以2.6的C_V运行的襟翼的前缘开始，以AJVG的形式进行流量控制大约30％x / c可使襟翼上表面边界层重新附着，从而恢复原始襟翼的性能。襟翼挠度增加的实验表明，所提出的流量控制模型定义的性能边界是有效的。对执行器间距影响的研究表明，孔间距比为20时，系统增益最佳。在实验规模上，使用C_V或C_μ作为相似性参数，结果会以合理的速度很好地崩溃。对A320型飞机的实验结果的临时缩放表明，基于速度比缩放比例，将需要大约0.5％的发动机着陆质量流量，而基于动量比缩放比例，则需要8％的发动机着陆质量流量。

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  • 来源
    《Journal of Aircraft》 |2006年第5期|p.1589-1593|共5页
  • 作者

    W. J. Crowther;

  • 作者单位

    University of Manchester, Manchester, M60 1QD, United Kingdom;

  • 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 航空;
  • 关键词

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