The development of a wing-tip vortex of a rectangular, square-tipped wing having a NACA 0012 airfoil at a chord Reynolds number $Re_{c_{w}}=2\times 10^{5}$ , under the effect of synthetic jet actuation, was experimentally studied. Five control configurations were considered: case C1 with momentum coefficient $C_{\unicode[STIX]{x1D707}}=0.001$ and actuation frequency $F^{+}=0.075$ ; case C2 with $C_{\unicode[STIX]{x1D707}}=0.001$ and $F^{+}=0.15$ ; case C3 with $C_{\unicode[STIX]{x1D707}}=0.001$ and $F^{+}=0.3$ ; case C4 with $C_{\unicode[STIX]{x1D707}}=0.001$ and $F^{+}=0.6$ ; and case C5 with $C_{\unicode[STIX]{x1D707}}=0.001$ and $F^{+}=1.2$ . Under the most effective configuration, case C3, the vortex was stretched and appeared to be diffuse with a nearly 40 % decrease in the peak circumferential velocity and 50 % decrease in the core axial vorticity. The vortex core radius largely broadened suggesting that the lower-frequency control configuration allowed the synthetic jet to travel larger distances into the vortex bringing turbulent structures within its core resulting in increased mixing and subsequently a more diffuse vortex.

中文翻译：

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主动流动控制对翼尖涡蜿蜒的影响

在合成作用下，在弦雷诺数 $Re_{c_{w}}=2\times 10^{5}$ 处，具有 NACA 0012 翼型的矩形、方形翼的翼尖涡的发展射流驱动，进行了实验研究。考虑了五种控制配置：具有动量系数 $C_{\unicode[STIX]{x1D707}}=0.001$ 和驱动频率 $F^{+}=0.075$ 的案例 C1；案例 C2 与 $C_{\unicode[STIX]{x1D707}}=0.001$ 和 $F^{+}=0.15$ ；案例 C3 与 $C_{\unicode[STIX]{x1D707}}=0.001$ 和 $F^{+}=0.3$ ；案例 C4 与 $C_{\unicode[STIX]{x1D707}}=0.001$ 和 $F^{+}=0.6$ ；和案例 C5 与 $C_{\unicode[STIX]{x1D707}}=0.001$ 和 $F^{+}=1.2$ 。在最有效的配置下，案例C3，涡流被拉伸并且似乎是扩散的，峰值圆周速度下降了近 40%，核心轴向涡度下降了 50%。涡核半径大大扩大，这表明较低频率的控制配置允许合成射流进入涡旋的距离更长，从而在其核心内带来湍流结构，导致混合增加，随后产生更扩散的涡旋。