Abstract A series of wind tunnel tests were performed to investigate the effect of turbulent inflows on the aerodynamic characteristics of variously modified leading-edge protuberanced (LEP) wing configurations at various turbulence intensities. A self-developed passive grid made of parallel arrays of round bars was placed at different locations of the wind tunnel to generate desired turbulence intensity. The aerodynamic forces acting over the baseline straight leading-edge model and the modified small, medium and high LEP wing configurations were obtained from the surface pressure measurements made over the wing at different turbulence intensities using MPS4264 Scanivalve simultaneous pressure scanner corresponding to a sampling frequency of 700Hz. All the test models were tested for a wide range of angles of attack ranging between −45° ≤ α ​≤ ​45° at turbulence intensities varying between 0.51% ​≤ ​TI ​≤ ​4.92%. Results reveal that the time-averaged mean coefficient of lift (CL) increases with the increase in the turbulence intensity associated with smooth stall characteristics rendering the modified LEP test models advantageous. Furthermore, based on the surface pressure coefficients the underlying dynamics behind the stall delay tendency were discussed. Additionally, attempts were made to statistically quantify the aerodynamic forces using standard deviation at both the pre-stall and the post-stall angles.

中文翻译：

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不同湍流强度下各种改进的前缘突起（LEP）风力涡轮机叶片的气动特性

摘要 进行了一系列风洞试验以研究湍流流入对不同湍流强度下各种改进的前缘突起 (LEP) 机翼配置的空气动力学特性的影响。在风洞的不同位置放置由平行排列的圆棒组成的自主开发的被动网格，以产生所需的湍流强度。作用在基线直前缘模型和改进的小、中、高 LEP 机翼配置上的空气动力是从使用 MPS4264 Scanivalve 同步压力扫描仪在不同湍流强度下对机翼进行的表面压力测量中获得的700赫兹。所有测试模型都针对-45° ≤ α ≤ 45° 之间的大范围攻角进行了测试，湍流强度在 0.51% ≤ TI ≤ 4.92% 之间变化。结果表明，时间平均升力系数 (CL) 随着与平滑失速特性相关的湍流强度的增加而增加，从而使改进的 LEP 测试模型具有优势。此外，基于表面压力系数，讨论了失速延迟趋势背后的潜在动力学。此外，还尝试使用预失速和后失速角度的标准偏差对空气动力进行统计量化。结果表明，时间平均升力系数 (CL) 随着与平滑失速特性相关的湍流强度的增加而增加，从而使改进的 LEP 测试模型具有优势。此外，基于表面压力系数，讨论了失速延迟趋势背后的潜在动力学。此外，还尝试使用预失速和后失速角度的标准偏差对空气动力进行统计量化。结果表明，时间平均升力系数 (CL) 随着与平滑失速特性相关的湍流强度的增加而增加，从而使改进的 LEP 测试模型具有优势。此外，基于表面压力系数，讨论了失速延迟趋势背后的潜在动力学。此外，还尝试使用预失速和后失速角度的标准偏差对空气动力进行统计量化。