Wake Vorticity Measurements for Low Aspect Ratio Wings at Low Reynolds Number
Wake Vorticity Measurements for Low Aspect Ratio Wings at Low Reynolds Number
复制标题
低雷诺数下低展弦比机翼的尾流涡度测量
DOI：
10.2514/1.23096
复制
发表时间：
2007
影响因子：
2.2
通讯作者：
M. Ol
中科院分区：
文献类型：
--
作者：
S. M. Kaplan;A. Altman;M. Ol
在水洞中，在雷诺数为8000和24,000时，采用染料喷射和数字粒子图像测速技术，在近尾流的横流平面内，对矩形、半椭圆和三角翼的平面形状的小展弦比机翼的尾涡结构进行了研究。速度数据被用来计算升力通过环量和有效跨度，并与力平衡测量和经典的无粘理论的结果进行了比较。研究的目的是评估低雷诺数效应如何影响叶尖涡环流升力系数的测量，测量值与小展弦比机翼升力曲线斜率的各种理论模型的拟合程度，以及展弦比和平面形状面积保持不变时，平面形状对升力系数的影响程度。所有模型均为方形边缘的薄平板
Trailing vortex structure of low aspect ratio wings was studied in a water tunnel at Reynolds numbers of 8000 and 24,000 using dye injection and digital particle image velocimetry in cross-flow planes in the near wake, for rectangular, semi-elliptical, and delta-wing planforms. The velocity data were used to calculate lift via circulation and effective span, and the results were compared with force balance measurements and classical inviscid theory. The objectives of the study were to assess how low-Reynolds number effects might affect the measurement of lift coefficient from tip-vortex circulation, how well the measurements fit the various theoretical models of lift curve slope for low aspect ratio wings, and the extent to which planform shape affects lift coefficient while aspect ratio and planform area are kept constant. All models were thin flat plates with square edges