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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。
In this paper, the wind tunnel experiment is carried out to suppress the wingtip vortex by using DBD plasma energy injection. The vortex flow field downstream of the swept wing under the influence of three kinds of plasma actuators was measured by using the PIV particle imaging velocimetry technique. Combined with the aerodynamic changes of the rectangular wing before and after the plasma action, the plasma suppression wing Vortex effect. The experimental results show that the plasma actuator is arranged on the upper and lower wingtips of the wing tip, and the energy induced by the induced vortical flow field induced by the plasma can effectively delay the flow separation on the wing tip and suppress the wingtip Vortex, increase lift, improve the resistance ratio. When the flow separation is small at the tip of the wing, the effect of the plasma suppression wing tip vortex intensity is obvious; it still has a certain effect under a large attack angle; and its effect is related to the structure of the plasma generator. Therefore, by optimizing the structure of the plasma actuator and selecting a suitable plasma actuator at the wing tip surface, the effect of suppressing wingtip vortex can be better improved.