高速风洞等离子体流动控制实验技术研究

Research on the experimental technology of plasma active flow control in high speed wind tunnel

针对开展等离子体高速流动控制研究的技术需求,通过专用模型及实验机构设计、绝缘密封走线、多层电磁屏蔽等技术手段,建立了一套适用于高速风洞的等离子体流动控制系统,提出了等离子体高速流动控制风洞实验的技术规范和运行策略,并初步探索了等离子体激励对二元翼型绕流的控制规律。采用该技术后,解决了高压电缆的绝缘、密封走线问题,模型与实验机构的感应电压减小90%以上。风洞实验结果表明:实验系统运行稳定,实验数据可靠,等离子体激励对Ma=0.2的流动可实现有效控制;施加等离子体激励后,NACA0012翼型的流动分离明显减弱,升力增大,阻力减小,临界失速迎角增大2°,最大升力系数增大4%,总体气动性能得到显著提升。

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＆#176;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.