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Mitigation of Dynamic Stall over a Pitching Finite Wing Using High-Frequency Actuation

机译：使用高频驱动缓解俯仰有限机翼上的动态失速

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摘要

A novel high-frequency flow control strategy for mitigation of dynamic stall is demonstrated for the case of a finite wing using high-fidelity wall-resolved implicit large-eddy simulations. A NACA 0012 wing of aspect ratio AR=4 is considered at freestream Mach number M infinity=0.1 and chord Reynolds number Rec=2x105. The wing undergoes an oscillatory pitching motion with reduced frequency k=pi/16 and maximum angle of attack alpha max=22 degrees, resulting in deep dynamic stall for the baseline case. Very-high-frequency (Stf=fc/U infinity=50.0) spanwise uniform low-amplitude pulsed forcing is imparted through a zero-net mass flow blowing/suction slot located on the wing lower surface near the leading edge. The imposed small fluctuations are amplified by the laminar separation bubble (LSB) and inhibit LSB bursting and the formation of large-scale dynamic stall vortices. By maintaining effectively attached flow throughout the pitching cycle, actuation provides a significant reduction in the cycle-averaged drag and in the force and moment excursions. In addition, the negative (unstable) net-cycle pitch damping found in the baseline case is eliminated.
机译：通过使用高保真壁解析隐式大涡模拟，对有限机翼的情况展示了一种新颖的减轻动态失速的高频流控制策略。纵横比AR = 4的NACA 0012机翼被视为自由流马赫数M infinity = 0.1和弦雷诺数Rec = 2x105。机翼经历了摆动俯仰运动，其频率降低了k = pi / 16，最大迎角αmax = 22度，导致基线情况下发生了深度动态失速。通过位于机翼下表面靠近前缘的零净质量流量吹/吸槽，可在跨度方向上产生非常高的频率（Stf = fc / U infinity = 50.0）均匀低振幅脉冲强迫。施加的小波动被层流分离气泡（LSB）放大，并抑制LSB爆裂和大规模动态失速涡流的形成。通过在整个俯仰周期中保持有效附着的流量，致动可显着降低周期平均阻力以及力和力矩偏移。此外，消除了基线情况下的负（不稳定）净周期螺距阻尼。

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  • 来源
    《AIAA Journal》 |2020年第1期|51-60|共10页
  • 作者

    Visbal Miguel R.; Garmann Daniel J.;

  • 作者单位

    Air Force Res Lab Aero Sci Ctr Wright Patterson AFB OH 45433 USA;

  • 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
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