等离子体激励控制后掠翼前缘集中涡破裂机理及应用研究

项目名称： 等离子体激励控制后掠翼前缘集中涡破裂机理及应用研究

项目编号： No.10872021

项目类型： 面上项目

立项/批准年度： 2009

项目学科： 金属学与金属工艺

项目作者： 张攀峰

作者单位： 北京航空航天大学

项目金额： 45万元

中文摘要： 本项目通过对等离子体推迟前缘涡破裂并提高三角翼气动特性的风洞流动显示和测力研究，揭示了等离子激励与三角翼前缘涡相互作用的机制。并通过在无人机后缘布置等离子体激励器，利用科恩达附壁效应，改变机翼尾缘的流动状态，实现了低速条件下无人机的增升和俯仰的无铰链控制。提出了等离子体Gurney襟翼增升技术，并通过数值模拟和实验进行了验证，指出等离子体在机翼后缘产生的射流，可以有效改变机翼后缘的Kutta条件，实现全弦长加载，从而提高机翼的升力系数。

中文关键词： 等离子体激励；流动控制；空气动力学；

英文摘要： The project investigated the aerodynamics characteriscits of delta wing with plasma actuation by flow visulization and force measurment in wind tunnel, the mechanism of the interation of plamsa actuator with the leading edge vortex of delta wing was discussed. The plasma actuators were also set on the trailing edge of UAV, by using the Coanda effect, the boundary layer was induced to adhere on the tailing edge surface, so the lift coefficient and pitching moment can be adjusted by plamsa actuator in low speed flow condition. A new lift enhancment technique-plamsa Gurney flap was aslo proposed and validated by numerical simulation and experiment. The Gurney flap increased the load through the whole chord length by changing the Kutta condition of trailing edge of the wing, so the lift coefficient of the wing can be increased.

英文关键词： plasma actuation；flow control；aerodynamics