空气动力学学报Issue(6)：823-827,5.DOI:10.7638/kqdlxxb-2014.0055
等离子体用于飞翼布局模型增升减阻试验研究
Experimental investigation on flying wing lift enhancement and drag reduction by plasma
于金革 1牛中国 1梁华 2管佳明 1胡秋琦1
作者信息
- 1. 中国航空工业空气动力研究院，黑龙江 哈尔滨 150001
- 2. 空军工程大学 航空航天工程学院 等离子体动力学重点实验室，陕西 西安 710038
- 折叠
摘要
Abstract
Under the condition of wind speed of 30 m/s or 40 m/s,the effect of the parameter of the voltage and the number of actuated electrode couples as well as the position of the plasma aerodynamic actuation on the lift enhancement and drag reduction of a flying wing are investigated by means of force-balance tests in the wind tunnel after the nanosecond pulse die-lectric barrier discharge plasma actuator was installed.The force test results show that,compared with the voltage and the number of actuated electrode couples,the position of the plasma aerodynamic actuation determines flow control effect mainly.Compared with other control position,plasma inhibites model′s leading edge vortices seperation obvious.Plasma actuator injectes energy to the boundary layer of fluid so the surface flow separation is delayed to larger angle of attack for the flying wing,the maximum lift coefficient and stall angle are also efficiently increased,and drag coefficient is reduced at the same time.Under certain test conditions,the maximum lift coeffi-cient increases 13.2% from 0.97 to 1.1,stall angle increases 4°from 17.4°to 21.4°and drag coefficient reduces 24.6%,and the more energy the plasma actuator is increased,the more obvi-ous effect the plasma actuator will generate.关键词
等离子体/介质阻挡放电/飞翼布局/增升减阻/试验研究Key words
plasma/dielectric barrier discharge/flying wing/lift enhancement and drag reduction/wind tunnel test分类
航空航天引用本文复制引用
于金革,牛中国,梁华,管佳明,胡秋琦..等离子体用于飞翼布局模型增升减阻试验研究[J].空气动力学学报,2015,(6):823-827,5.
