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首页> 外文期刊>Journal of Aircraft >Compressibility and Excitation Location Effects on High Reynolds Numbers Active Separation Control
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Compressibility and Excitation Location Effects on High Reynolds Numbers Active Separation Control

机译：可压缩性和激发位置对高雷诺数主动分离控制的影响

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摘要

The effects of compressibility and excitation slot location on active separation control at high Reynolds numbers are explored. The model, which was tested in a cryogenic pressurized wind tunnel, simulates the upper surface of a 20% thick Glauert-Goldschmied-type airfoil at zero angle of attack. The boundary layers on the model are turbulent because the tunnel sidewall boundary layer flows over it. Without control, the flow separates at the highly convex area of the model and a large turbulent separation bubble is formed. Periodic excitation was applied to control the separation bubble. Two alternative blowing slot locations, as well as the effect of compressibility and steady suction or blowing, were studied. During the test, the chord Reynolds numbers ranged from 1.1 x 10~7 to 3 x 10~7 and the Mach numbers ranged from 0.25 to 0.7. It was found that excitation must be introduced slightly upstream of the separation region at low Mach number. Introduction of excitation upstream of the shock wave is more effective than at its foot. Compressibility reduces the ability of steady mass transfer and periodic excitation to control the separation bubble, but periodic excitation has an effect on the integral parameters, which is similar to that observed in low Mach numbers. Blowing becomes more effective than suction at transonic speeds, whereas the opposite was found in low Mach numbers. The data presented provide a proper validation case for unsteady numerical design tool that will enable exploring the full potential of unsteady flow control.
机译：探索了可压缩性和激发槽位置对高雷诺数下主动分离控制的影响。该模型在低温加压风洞中进行了测试，它模拟了20％厚的Glauert-Goldschmied型翼型在零迎角下的上表面。模型上的边界层是湍流的，因为隧道侧壁边界层在其上流动。在没有控制的情况下，流体在模型的高凸区域处分离，并形成了大的湍流分离气泡。施加周期性激发以控制分离气泡。研究了两个可选的吹气槽位置，以及可压缩性和稳定抽吸或吹气的效果。在测试过程中，和弦雷诺数的范围从1.1 x 10〜7到3 x 10〜7，马赫数的范围从0.25到0.7。已经发现，在低马赫数下，必须在分离区域的上游稍微引入激发。在激波上游引入激励比在激波足部更有效。可压缩性降低了稳定传质和周期性激发来控制分离气泡的能力，但是周期性激发对积分参数有影响，这与在低马赫数下观察到的相似。在跨音速下吹气比吸气更有效，而在低马赫数下却相反。所提供的数据为非稳态数值设计工具提供了适当的验证案例，这将有助于探索非稳态流量控制的全部潜力。

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  • 来源
    《Journal of Aircraft》 |2003年第1期|p.110-119|共10页
  • 作者

    Avi Seifert; LaTunia G. Pack;

  • 作者单位

    Tel-Aviv University, 69978 Ramat Aviv, Israel;

  • 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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