Effect of Tip Vortices in Low-Reynolds-Number Poststall Flow Control
Effect of Tip Vortices in Low-Reynolds-Number Poststall Flow Control
复制标题
叶尖涡对低雷诺数失速流动控制的影响
DOI：
10.2514/1.40615
复制
发表时间：
2009
期刊：
影响因子：
2.5
通讯作者：
T. Colonius
中科院分区：
文献类型：
--
作者：
K. Taira;T. Colonius
数值研究了定常吹气在雷诺数为300时小展弦比矩形平板机翼三维失速流动中的应用。这项研究的目的是探索
通过直接改变尾迹涡的动力学来增强升力的技术。在不同的组合中
强制位置和方向考虑，我们确定了两种配置，提供显著的升力增强。在……里面
在这些情况下，驱动似乎加强了尖端涡旋，以增加向下诱导速度在
前缘涡流。这反过来又将低压核心直接移动到机翼顶面上方，从而大大
提升升力。
We numerically investigate the application of steady blowing to three-dimensional stalled flows around low-aspect-ratio rectangular flat-plate wings at a Reynolds number of 300. The objective of this study is to explore
techniques to enhance lift by directly modifying the dynamics of the wake vortices. Out of various combinations of
forcing location and direction considered, we identify two configurations that provide significant lift enhancement. In
these cases, actuation appears to strengthen the tip vortices for increased downward induced velocity upon the
leading-edge vortices. This in turn moves the low-pressure core directly above the top surface of the wing to greatly
enhance lift.