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Experimental study of vortex generators effects on low Reynolds number airfoils in turbulent flow

机译：涡流发生器对湍流中低雷诺数翼型影响的实验研究

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In the present work, we study the aerodynamic effects of triangular vortex generators, as passive flow control devices, placed on the upper surface of an airfoil submitted to a low Reynolds number turbulent flow. In the experiments, different configurations of those devices have been studied. An Eppler 387 airfoil was used. The tests were performed in a turbulent boundary layer wind tunnel using a two component aerodynamic balance and flow visualisation systems. Turbulent flow characterisation was made by means of hot wire anemometry. Calculations of local turbulent intensity as well as temporal and spatial turbulent scales were made. Vortex generators were located at 10% and 20% of the airfoil chord from the leading edge, modifying its angle of incidence refereed to the free stream. The results show changes in the aerodynamic section coefficients, C_1, C_d and C_1 for the different vortex generator configurations. Neither hysteresis effects, nor leading edge bubbles were found in the experiments.
机译：在目前的工作中，我们研究作为被动流量控制装置的三角涡流发生器的气动效应，该涡流发生器置于低雷诺数湍流的翼型上表面。在实验中，已经研究了那些设备的不同配置。使用了Eppler 387机翼。测试是在湍流边界层风洞中进行的，使用了两部分空气动力学平衡和流量可视化系统。借助热线风速测定法对湍流进行了表征。进行了局部湍流强度以及时空湍流尺度的计算。涡流发生器位于距机翼前缘10％和20％的翼弦上，从而改变了其与自由流相关的入射角。结果显示了不同涡流发生器配置的空气动力学截面系数C_1，C_d和C_1的变化。在实验中既没有发现磁滞效应，也没有发现前沿气泡。

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