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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建立了带柔性后缘自适应机翼模型和带刚性偏转后缘的传统机翼模型，从升阻特性和力矩特性以及操纵效率对它们进行了比较研究。

This paper aims at presenting an investigation into aerodynamics and control reversal characteristics of adaptive wings with seamless, variable camber, flexible trailing edge.

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将高速滑体制成相似的机翼模型，进行风洞试验，即可测定滑坡凌空飞行的空气动力学参数，从而计算大型高速滑坡凌空飞行的空气动力升力、飞行速度和飞行距离等。

If we make a wing model which is similar to sliding mass, we can determine aerodynamic parameters by the wind tunnel testing and thus calculate the lift.

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