Voluminous research exists on the effect of combination of low Reynolds number flow over low aspect ratio flat plate wings for usage in micro-aerial vehicles and UAVs, as they also fly under similar conditions and combination of low aspect ratio and low Reynolds number. It has been well established by many researchers (Torres and Mueller in AIAA 42(5):865–873, 2004; Okamoto and Azuma in AIAA 49(6):1135–1150, 2011; Mizoguchi and Itoh in AIAA 51(7):7–52, 2013; Shields and Mohseni in AIAA 50(1):85–99, 2012; Mizoguchi and Kajikawa in Trans Jpn Soc Aero Sp Sci 59(2):56–63, 2016; Pelletier and Mueller in J Aircr 37(5):825–832, 2000; Liu and Hsiao in J Mech 28(01):77–89, 2012; Taira and Colonius in J Fluid Mech 623:187–207, 2009) that low aspect ratio wings in low Reynolds number flow gives a higher lift coefficient and stall angle is also increased which is quite different from the high aspect ratio wing. Also, it is a well-established fact in the existing literature that linear theories cannot be applied as in case of high aspect ratio wings because of non-linear increase in lift coefficient. The reason for such increase in lift and stall angle has been attributed to wingtip vortices that become prominent in low aspect ratio wings called the vortical lift which keeps on increasing up to a certain high angle of attack till it interacts with the separation bubble. In the past, very limited work has been done to study the vortices and their contribution in enhancement of aerodynamic characteristics. In the present work, flat plate model with corrugations at an aspect ratio (AR) of 1.0 are studied and compared with flat plate wing of AR 1.0; also flow visualization in water tunnel has been carried out at Reynolds number of 10 2 to ascertain the flow physics involved.

中文翻译：

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低纵横比波纹翼上的低雷诺数流

关于低纵横比平板机翼上低雷诺数流组合用于微型飞行器和无人机的影响存在大量研究，因为它们也在类似的条件下飞行以及低纵横比和低雷诺数的组合。许多研究人员已经很好地建立了它（AIAA 42(5):865–873, 2004 中的 Torres and Mueller；AIAA 49(6):1135–1150, 2011 中的 Okamoto 和 Azuma；AIAA 51(7) 中的 Mizoguchi 和 Itoh :7–52, 2013; Shields and Mohseni in AIAA 50(1):85–99, 2012; Mizoguchi and Kajikawa in Trans Jpn Soc Aero Sp Sci 59(2):56–63, 2016; Pelletier and Mueller in J Aircr 37(5):825–832, 2000; Liu and Hsiao in J Mech 28(01):77–89, 2012; Taira and Colonius in J Fluid Mech 623:187–207, 2009）低雷诺数流中的低展弦比机翼提供了更高的升力系数，并且失速角也增加了，这与高展弦比机翼完全不同。此外，在现有文献中，由于升力系数的非线性增加，线性理论不能应用于高展弦比机翼的情况是一个公认的事实。升力和失速角的这种增加的原因归因于翼尖涡流在低展弦比机翼中变得突出，称为涡流升力，它不断增加到一定的高迎角，直到它与分离气泡相互作用。过去，研究涡流及其对增强空气动力学特性的贡献的工作非常有限。在目前的工作中，研究了具有纵横比（AR）为1.0的波纹的平板模型，并与AR 1.0的平板翼进行了比较；还以雷诺数 10 2 进行了水隧道中的流动可视化，以确定所涉及的流动物理。