An experimental investigation is conducted to study the effect of multiscale endplates on the wing-tip vortex and wing aerodynamic performance at Reynolds numbers of 215,000 and 244,000 based on the wing mean chord of a NACA 0012 half-span wing. Two groups of endplates are tested. The first group has three different fractal patterns applied along the top edge of the endplate, while the second group has three different two-scale patterns applied to its outboard surface. It is experimentally shown that both geometry modifications produce a weaker and less coherent vortex. Moreover, while a peak in the power spectral density of the fluctuating axial velocity at the vortex core at Strouhal numbers between 3 and 10 is observed for the plain endplates of both groups, it vanishes for the multiscale endplates. This suggests that the multiscale endplates act on the vortex structure, making it less coherent through the production of smaller eddies as evidenced by the velocity spectra. The multiscale endplates also show potential improvements in terms of the wing aerodynamic efficiency, with the maximum $C_l/C_d$ being up to 11.1% larger than for the corresponding plain endplate.

根据NACA 0012半跨式机翼的机翼平均弦，进行了实验研究，以研究雷诺数分别为215,000和244,000时多尺度端板对机翼尖端涡旋和机翼空气动力性能的影响。测试了两组端板。第一组具有沿端板顶部边缘施加的三种不同的分形图案，而第二组具有应用于其外侧表面的三种不同的两尺度图案。实验表明，两种几何形状修改都会产生较弱且不那么连贯的涡旋。而且，虽然在两组的普通端板上都观察到在Strouhal数为3到10的Strouhal数处在涡旋核心处的轴向速度波动的功率谱密度的峰值，但对于多尺度端板则消失了。这表明多尺度端板作用在涡旋结构上，从而通过产生较小的涡流而使其不连贯，如速度谱所证明的那样。多级端板还显示出机翼空气动力效率方面的潜在改进，最大$C_{升}/C_d$ 比相应的普通端板大11.1％。