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以太阳能飞机为背景,对低雷诺数翼型FX 63-137进行了折线型建模以拟合典型晶硅太阳能电池片对气动外形的影响,开展了气动数值模拟分析。首先引用“拟合优度”的定义描述本文折线型翼型轮廓与基准翼型(Baseline)的吻合度,并以此参数为变量建立5种折线型翼型模型;然后,采用计算流体力学(CFD)方法计算分析了不同雷诺数下各折线型翼型的气动特性,并着重研究了低雷诺数下折线型翼型的绕流机理;最后,基于工程应用实际的需求,提出了晶硅太阳能电池片的铺设方法也即折线型翼型设计思想准则,并进行算例验证。研究结果表明:低雷诺数条件下,折线型翼型升阻性能相比光滑翼型在一定程度上表现出了优势,但随着雷诺数的增加,升阻方面的优势逐渐消失;折线型翼型压力分布受各折线段长度影响,前缘吸力峰值、压力平台范围以及压力恢复区分布特征是决定折线型翼型气动性能的主要因素;通过设计的算例验证了本文提出的折线型翼型设计思想的可行性。
Taking the solar airplane as the background, the low Reynolds number airfoil FX 63-137 was modeled as a polygon to fit the aerodynamic shape of a typical crystalline silicon solar cell and the aerodynamic numerical simulation was carried out. Firstly, the definition of “goodness of fit” is used to describe the coincidence degree between the linear profile and the baseline, and five kinds of linear airfoil models are established based on this parameter. Then, The CFD method is used to calculate and analyze the aerodynamic characteristics of the airfoils with different Reynolds numbers, and the flow around the airfoil with the low Reynolds number is studied emphatically. Finally, based on the actual demand of engineering application, The laying method of the silicon solar cell is also the design guideline of the polygonal line airfoil, and carries on the example verification. The results show that, at low Reynolds number, the lift resistance of the profiled wing airfoil shows a certain degree of advantage over the smooth airfoil, but as the Reynolds number increases, the advantage of lift resistance gradually disappears. The pressure distribution is affected by the length of each broken line segment. The leading edge suction peak, the pressure platform range and the pressure recovery zone distribution are the main factors that determine the aerodynamic performance of the profiled airfoil. The numerical examples show that the proposed profiled airfoil Feasibility of design ideas.