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.
采用多项式迟滞非线性模型建立二元机翼气动弹性运动方程，并用数值积分法进行求解。
The dynamical equation of a two-dimensional airfoil with polynomial hysteresis nonlinearity in pitch is solved using Runge-Kutta time marching integration.
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