变弯度机翼准定常流动分离特性的实验研究
摘要
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 established 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.