振动二元翼流动显示水洞试验研究

A Flow Visualization Experiment on the Unsteady Flow Around Two-Dimensional Airfoil

本文是用流场显示的方法研究各种形式的机械激励对二元机翼大攻角流场的影响。得到的试验结果表明,所采用的机械激励对大攻角失速分离流动有强的控制作用。它清楚地反映了过去风洞试验结果的物理本质,也为今后的非定常增升效应研究明确了方向。

A flow visualization experiment is performed in water channel. By exerting some kinds of mechanical excitations, such as flap and rotating leading edge, on the flow field around a two-dimensional airfoil at high angle-of-attack, the unsteady flow effects are focused on. The experimental results show that the mechanical excitation adopted can strongly affect the separating flow around the stalled air-foil at high angle-of-attack. It clearly reveals the physical mechanism of the experimental results that we obtained earlier in wind tunnel, and shows a way for the followed researches on the high lift efficient effects due to the unsteady flow.