Dynamic stall flow control via a trailing-edge flap
Dynamic stall flow control via a trailing-edge flap
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DOI：
10.2514/1.17263
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发表时间：
2006-03-01
期刊：
影响因子：
2.5
通讯作者：
Lee, T
中科院分区：
文献类型：
--
作者：
Gerontakos, P;Lee, T
在Re = 1.65 × 10（5）时，研究了可动后缘襟翼（在振荡NACA 0015翼型的动载荷回路中）的影响。考虑了针对不同平坦）致动开始时间、持续时间和振幅的向上和向下平坦）偏转。表面压力测量结果表明，只有向上襟翼偏转才能减小低头俯仰力矩，襟翼偏转越大，减小力矩的机理就越有效。作动持续时间越短，过失速升力损失越小.最大低头俯仰力矩的减小是后缘襟翼下表面出现的吸气压力的结果。动态失速涡的形成和分离不受襟翼运动的影响，而涡的低压信号被向上襟翼偏转减小。在上升冲程中襟翼作动时间越晚，净扭转阻尼越大。最佳襟翼运动也进行了讨论。
Effects of a moveable trailing-edge flap (in the dynamic-load loops of an oscillating NACA 0015 airfoil were investigated at Re = 1.65 x 10(5). Both upward and downward flat) deflections for different flat) actuation start times, durations, and amplitudes were considered. Surface pressure measurements show that only upward flap deflections led to the reduction of nose-down pitching moment, and that the larger the flap deflection the more efficient the reduction mechanism was. The shorter (lie actuation duration the smaller the poststall lift loss. The reduction of the peak nose-down pitching moment was a consequence of the suction pressure appearing oil the lower surface of the trailing-edge flap. The formation and detachment of the dynamic-stall vortex was not affected by the flap motion, whereas the low-pressure signature of the vortex was reduced by the upward flap deflection. The later the flap actuation during the upstroke, the greater the net torsional damping was. Optimum flap motion is also discussed.