基于纳秒脉冲等离子体气动激励的翼型失速涡控制研究  

Research of Post-stall Vortex Control on Airfoil Based on Nanosecond Pulse Plasma Aerodynamic Actuation

作　　者：党维[1,2] 梁华 

机构地区：[1]中国飞行试验研究院,西安710089 [2]飞行仿真航空科技重点实验室,西安710089 [3]空军工程大学航空航天工程学院等离子体动力学实验室,西安710038 [4]西北工业大学航空学院,西安710072

出　　处：《高压电器》2017年第12期74-80,共7页High Voltage Apparatus

基　　金：国家自然科学基金资助项目(51476197);航空科学基金资助项目(20141396009);博士后科学基金资助项目(2014M562446);国防科技项目基金资助项目(2201058)~~

摘　　要：为了揭示纳秒脉冲等离子体气动激励与附面层耦合作用机制,首先开展了NACA0015翼型的大迎角粘性绕流数值模拟,比较了3种典型湍流模型(S-A模型、standard k-w模型和SST k-w模型)对计算结果的影响,分析得到了翼型的近场旋涡分离流动流场结构特性,并对升力特性进行了频谱分析,得到了翼型非定常流动特征频率。进一步开展了基于脉冲等离子体气动激励的翼型大迎角绕流的频率耦合的风洞实验,实验结果表明:当固定激励电压,纳秒脉冲的激励频率大于或等于流场旋涡脱落频率时,控制效果最好,可在来流速度为100 m/s、攻角为22°时,可将翼型的升力系数增大18.1%,阻力系数减小22.5%。研究结论有助于揭示纳秒脉冲等离子体气动激励进行涡控制的作用机理,从而提高纳秒脉冲等离子体气动激励涡控制的能力。Numerical simulations on NACA0015 airfoil at standard k-w, and SST k-w turbulence models to reveal high angles of attack were performed by using the S-A, the interaction of nanosecond pulse plasma aerodynamic actuation and boundary layer, and the effects of these three turbulence models on aerodynamic simulation accuracy were contrasted. Based on the calculated results, the structure of unsteady separated flow and the frequency spectrum of lift coefficient were analyzed, and the characteristic frequency of the unsteady flow around the airfoil was discovered. Then, wind tunnel experiment was conducted with the coupling between the actuation frequency and the vortex shedding frequency. The results indicate that the unsteady separated flow can be effectively controlled as the actuation frequency is not lower than the vortex shedding frequency, and the lift coefficient of the airfoil is increased by 18.1% and the drag coefficient is reduced by 22.5% when the coming flow velocity is 100 m/s and the angle of attack is 22°. This study may help to reveal the vortex control mechanism of nanosecond pulse plasma aerodynamic actuation and hence to enhance the vortex control ability.

关 键 词：纳秒脉冲 涡控制 等离子体气动激励 翼型 频率 

分 类 号：V211.41[航空宇航科学与技术—航空宇航推进理论与工程]