实验流体力学Issue(2)：27-31,44,6.DOI:10.11729/syltlx20130197
高速风洞等离子体流动控制实验技术研究
摘要
Abstract
In view of the technical requirements for the research on high speed flow control by plasma actuation,a set of plasma flow control system in high speed wind tunnel experiments was established through the special model and experimental installation design,sealed insulation alignment and multi-layer electromagnetic shielding techniques,then the technical specification and operation strategy were proposed for high speed flow control test by plasma actuation,and the control law of plasma actuation on a two element airfoil flow was explored.After using these techniques,the insulation,sealing alignment problems of high voltage cable were solved and the induced voltage between model and experimental installation decreases by more than 90%.The wind tunnel test results show that this system operates stably and the experimental data is relia-ble.The flow of Ma= 0. 2 can be controlled effectively by plasma actuation.The flow separation of NACA0012 airfoil is weakened significantly,and its lift increases and drag decreases.In addi-tion ,the critical stall angle of attack increases by 2°and the maximum lift coefficient increases by 4% due to the actuation.As a result,the overall aerodynamic performance of NACA0012 airfoil is improved.The results of this study provide an important reference and technical support for the further research on high speed flow control by plasma actuation.关键词
风洞实验/流动控制/等离子体/高速风洞/实验技术Key words
wind tunnel experiment/flow control/plasma/high speed wind tunnel/experimen-tal technology分类
航空航天引用本文复制引用
李峰,高超,郑博睿,王玉帅..高速风洞等离子体流动控制实验技术研究[J].实验流体力学,2014,(2):27-31,44,6.基金项目
国家自然科学基金资助项目（51107101）；总装预研基金（9140C42010212）；航空科学基金 （）
