本文简要地阐述了具有后缘控制面的二元机翼模型主动颤振抑制低速风洞试验的全过程。

This paper gives a brief description of the whole process of the low-speed wind tunnel test for active flutter suppression of a two-dimensional wing model with trailing edge control surface.

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本文对动失速型非定常分离流的主动控制方法在低速风洞中进行了实验研究。

An experimental investigation on the active control of dynamic stall type unsteady separated flow is carried out in the low speed wind tunnel using a phase averaged pressure measurement technique.

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风洞试验结果说明，采用颤振主动抑制控制系统后，机翼的颤振临界速度可提高37%。

The results of the wind tunnel test show the flutter critical speed of the wing model increases by 37% after the implementation of AFS system.

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