等离子体激励改善高升力机翼气动特性的仿真  

A Simulation of Improving Aerodynamic Characteristics of High-Lift Wing by Plasma Excitation

作　　者：王耀东 李军[1] 梁华[1,2] 肖良华[1] 魏彪[1] 

机构地区：[1]空军工程大学等离子体动力学重点实验室,西安710038 [2]西北工业大学航空学院,西安710072

出　　处：《空军工程大学学报（自然科学版）》2017年第6期1-7,共7页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：国家自然科学基金(61503302;51407197;51207169)

摘　　要：为探索大迎角下介质阻挡放电(DBD)对高升力机翼的作用机理,采用体积力模型和Eddy Viscosity Transport Equation全湍流模型耦合进行DBD激励改善其气动特性的模拟仿真研究。在来流速度45 m/s条件下,对比实验数据与仿真模型,验证了仿真模型的正确性;并采用该模型分析了机翼弦向、展向的2组截面流线图。结果表明:DBD激励位于机翼前缘能很好地提高高升力机翼大迎角气动特性,显著改善上翼面涡结构,促进分离流附体;可将机翼最大升力系数提高11.1%,失速迎角推迟2°,且随迎角增大,流动控制效果逐渐减弱直到消失。In order to explore the mechanism of dielectric barrier discharge at high angle of attack on the high-lift wing, the simulation of the aerodynamic characteristics of the high-lift wing with the coupling of the body force model and the Eddy Viscosity Transport Equation turbulence model is carried out. The sim- ulation model is validated by comparing the experimental data with the simulation model at the flow veloci- ty of 45 m/s. The model is used to analyze the streamlines of the chord-wise and span-wise sections of the wing. The results show that the DBD at the leading edge of the wing can obviously improve the aerody- namic characteristics of high-lift wing at high angle of attack, improve the vortex structure of the upper airfoil and control the separated flow. The maximum lift coefficient of the wing increases by 11.1% and the stall angle of attack is delayed 2°. And also, with the angle of attack increasing, the effect of flow con- trol is gradually weakened until disappearing.

关 键 词：等离子体 高升力机翼 流动分离 流动控制 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]