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.%在风速30 m／s、40 m／s 条件下，通过风洞天平测力试验，研究了飞翼布局模型上布置纳秒脉冲介质阻挡放电等离子体激励器后，等离子体激励电压、激励电极数目和激励位置变化对飞翼布局模型增升减阻的效果影响。研究表明，与激励电压和激励电极数目相比，激励位置对流动控制的效果有决定性的影响，同时相对于其他控制位置，等离子体激励抑制模型翼面前缘涡分离效果明显；等离子体激励启动后，通过向边界层内的流体注入能量，推迟了飞翼布局模型翼面大迎角时的流动分离，提高了模型的最大升力系数 CLmax 和失速迎角αs ，降低了阻力系数CD ；在一定试验条件下，施加等离子体气动激励后，最大升力系数 CLmax 由0．97增大到1．1，增大13．2％，失速迎角αs 由17．4增大到21．4，推迟了4°，阻力系数 CD 最大减小量达到24．6％，且随等离子体激励器能量的增加，激励效果越显著。
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