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研制了一种可实现弯度主动变形的机翼模型,搭建了相关的风洞测力及流场显示实验平台.低速风洞测力实验揭示了机翼弯度连续准定常变形下的流动分离特性,发现其与固定弯度下的流动分离有着显著区别,采用前缘和尾缘两种分离机制分析和解释了造成这种差异的原因.相关的流场测量结果验证了上述解释.在流动分离条件下,研究表明可变形飞行器外围流场结构不仅与当前时刻的飞行器外形及来流条件有关,而且还和流场变化的历史过程相关.
A wing model that can realize active camber deformation is developed, and the relevant experimental platform for wind force measurement and flow field display is set up.Low speed wind tunnel force test reveals the flow separation characteristics of the wing camber under continuous quasi-steady deformation, It is found that there is a significant difference between them and the flow separation under fixed camber, and the reasons for this difference are analyzed and explained by the two separation mechanisms of the leading edge and the trailing edge.The relevant flow field measurement results verify the above explanation.Under the conditions of flow separation The research shows that the structure of the flow field around the deformable aircraft is not only related to the current aircraft shape and flow conditions, but also to the historical process of flow field changes.