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A flow physics study of flap-mounted vortex generators on a multi-element airfoil.

机译：多翼型机翼上装有襟翼的涡流发生器的流动物理研究。

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Vortex generators are a commonly used aerodynamic “fix” for flow separation problems. They are typically used to remedy flow separation due to design shortcomings or changes in operating conditions that exceed the original design point.; Flow separation is often encountered with high lift systems. Flaps and slats can be difficult to design due to complicated flow phenomena and large Reynolds number effects. Previous research has indicated the effectiveness of vortex generators in correcting flow separation over a flap. In fact, significant aerodynamic performance improvements were predicted for high-lift systems that incorporate vortex generators in the original design. Before this may be attempted, a better understanding of vortex generator flow physics must be obtained for the development of appropriate design tools and analysis methods.; The research contained herein is focused on a detailed flow physics study of vortex generators mounted to the flap of a three-element high-lift airfoil. Detailed velocity measurements taken using a three-component laser Doppler velocimeter were used to vortex/boundary layer interactions and global flowfield effects. The full Reynolds stress tensor and mean velocity field was measured in addition to surface pressures. Three basic vortex generator arrangements were studied: upflow, downflow, and corotating.; Although not optimized, all three types of vortex generators were effective at eliminating boundary layer separation. The vortices demonstrated a tendency to rise from the flap surface regardless of orientation and decayed rapidly, with cross-stream vorticity dropping below measurable levels by 75% flap chord. However, the embedded vortices produced significant perturbations in the turbulence field and mean flow of the flap boundary layer that persisted to the flap trailing edge.
机译：涡流发生器是解决流分离问题的常用气动“解决方案”。它们通常用于补救由于设计缺陷或超出原始设计点的工作条件变化而引起的流分离。高扬程系统经常遇到流分离。由于复杂的流动现象和较大的雷诺数效应，襟翼和板条可能很难设计。先前的研究表明，涡流发生器在校正襟翼上的流分离方面是有效的。实际上，对于在原始设计中结合了涡流发生器的高升力系统，人们预计其空气动力学性能将得到显着改善。在尝试进行此操作之前，必须获得对涡流发生器流动物理学的更好理解，以开发适当的设计工具和分析方法。本文包含的研究重点是对安装在三元件高升力机翼襟翼上的涡流发生器进行详细的流动物理研究。使用三分量激光多普勒测速仪进行的详细速度测量被用于涡旋/边界层相互作用和整体流场效应。除了表面压力外，还测量了整个雷诺应力张量和平均速度场。研究了三种基本的涡流发生器布置：上流，下流和同向旋转。尽管没有优化，但所有这三种类型的涡流发生器在消除边界层分离方面均有效。无论方向如何，涡流都表现出从皮瓣表面上升的趋势，并且迅速衰减，横流涡流下降到可测量水平以下，降低了75％的皮瓣弦。然而，嵌入的涡流在湍流场中产生了显着的扰动，并持续到襟翼后缘的襟翼边界层的平均流量。

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