等离子抑制翼尖涡实验研究

该文对利用DBD等离子体注入能量抑制翼尖涡进行了风洞试验研究。通过采用PIV粒子成像测速技术测量了三种不同结构的等离子体激励器影响下的后掠翼下游的尾涡流场，并结合矩形机翼在等离子作用前后的气动力变化，来判断等离子体抑制翼尖涡的效果。试验结果表明:在机翼翼梢的上下表面处布置等离子体激励器，通过等离子体产生的定向诱导气流形成诱导涡对流场注入能量，可以有效地延缓翼梢上翼面流动分离，抑制翼尖涡，增加升力，提高升阻比。在翼尖处流动分离较小时，等离子体抑制翼尖涡强度的效果明显；在大攻角下仍具有一定的作用；其效果与等离子体发生器的结构有关。因此，通过优化等离子体激励器结构，选择合适的等离子体激励器在翼梢表面的安放位置，可以更好地提高抑制翼尖涡的效果。

STUDY ON EXPERIMENTS FOR SUPPRESSING WINGTIP VORTICES WITH PLASMA

The wind tunnel experiment on suppressing wingtip vortices (WTV) through adding energy with DBD plasma has been conducted in the paper. The WTV flow field of a swept wing has been visualized by PIV and the aerodynamic forces of a rectangular wing have been measured, in the condition of using three different kinds of plasma actuators respectively. The results show that the WTV may be suppressed and the separation on the upper wingtip surface may be delayed because the energy of the vortex induced by the plasma (VIP) is added into the flow field, which increases the lift and the ratio of lift to drag at a small angle of attack (AOA) effectively. Even at large AOA, the effect of plasma still appears. The effects are related to the structures of the plasma actuators. It can be obtain better results to suppress the WTV through optimizing the design of the plasma actuators and choosing the appropriate placement to install the actuators on wingtip surface.