摘要
为了研究等离子体射流环量控制对翼型气动特性的作用机理、影响规律和控制效费比,基于等效体积力耦合雷诺平均N-S方程的数值计算方法进行仿真,研究了不同后缘半径、单组激励器位置及双组激励器布置方式对翼型气动特性和流场特性的影响规律。结果显示中等后缘半径,两组激励器反向对称布置在上下翼面优化位置时,环量控制效费比有显著提升。研究表明中等后缘半径翼型的后缘流体离心力和压力梯度相对平衡,等离子体射流带动上翼面外流发生偏折,增升效果较好。优化后双组激励器作用形成了等离子体射流的串联,有效诱导脱体尾涡向下翼面移动,分离点下移,环量和升力增加明显。研究结果为后续实验研究提供了理论基础。
In order to find out the interaction mechanism, influence law and the lift augmentation efficiency of the plasma circulation control on airfoil aerodynamic characteristics, the influence law of different trailing-edge radius, single actuator position and arrangement mode of double actuators on the airfoil aerodynamic characteristics and flow field characteristics is investigated, by adding the equivalent volume force to the Reynolds-averaged Navier-Stokes equations. The result shows that the lift augmentation efficiency improves markedly by using the optimized medium trailing-edge radius model and applying two groups of plasma actuators reversely arranged on the upper and lower surface. The research shows that the profile with medium trailing-edge radius is comparatively good in lift enhancement effect because its centrifugal force and pressure gradient are balaced, and the plasma actuation jet drives the upper surface outflow deflected by guiding the couple of shed vortex moving to lower surface. The optimized double plasma actuators can make plasma actuation jets cascade, guide the couple of shed vortices moving to lower surface, and push the separation point down, thus causing the obvious behavior of profilers circulation and lift enhancement. The results provide a theoretical basis for subsequent experimental study.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2017年第3期9-15,共7页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国家自然科学基金(11402301)
陕西省自然科学基金(2015JM1005)
关键词
等离子体环量控制
翼型
后缘半径
双激励器
plasma circulation control
airfoil
trailing edge radius
double actuators
