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.
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 tests are conducted on a wing model with large aspect ratio.
试验是在大展弦比机翼颤振模型上进行的。
The ASE system for a wing model is applied to reveal the mechanism of the method by comparing the full model with the reduced order model.
以机翼气动伺服弹性系统为对象，比较了降阶前后模型变化情况。
On the basis of former rigid wing model and consideration of the velocity change and the distortion of wing plane, a flapping model is developed.
在原有匀速刚性模型的基础上，提出考虑了扑翼扑动速率变化和形状变化的柔性扑翼模型，使之更接近鸟翼真实扑动情况。
An optimization method of flutter wing model was developed and was used in many aspects of model designing, providing an efficient design method in engineering.
在此基础上建立了完整的机翼颤振模型工程优化设计方法，使该方法能够应用在模型设计的很多方面，为工程设计提供了一种有效的手段。
The phenomena "limit cycle" occurred in wind tunnel test for active flutter suppression of a wing model are numerically explained using Harmonic Balance Method.
本文采用谐波平衡法，定量地解释了机翼颤振主动抑制风洞试验中出现的极限环现象。
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.
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.
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。
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