变弯度机翼准定常流动分离特性的实验研究

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．

Experimental investigation on the quasi-steady flow separation behaviors of a variable camber wing

A test model of variable camber wing is developed as the first step of the work, which is capable of enough camber variation with acceptable mechanical stability and control accuracy. Corresponding experimental platform is esta- blished to conduct the aerodynamic load measurements and related flow visualization. Plentiful tunnel experiments depict distinction on the aerodynamic characteristics between the steady and quasi-steady flow separation behaviors. The distinction is interpreted with two types of stall mechanisms caused by the camber deformation： the leading-edge stall and the trailing-edge stall. Under the circumstance of flow separation, the morphing aircraft＇s flow structure depends not only on the current boundary conditions but also relates with the previous history.