下表面射流对翼型气动性能影响的数值模拟  

Numerical simulation of influence of jet at lower surface on aerodynamic performance of airfoil

作　　者：付云豪 章卫国[1,2] 史静平[1,2] 谭艺 FU Yunhao;ZHANG Weiguo;SHI Jingping;TAN Yi(School of Automation,Northwestern Polytechnical University,Xi’an 710072,China;Key Laboratory of Flight Control and Simulation Technology(Northwestern Polytechnical University),Shaanxi Province,Xi’an 710072,China)

机构地区：[1]西北工业大学自动化学院,西安710072 [2]陕西省飞行控制与仿真技术重点实验室(西北工业大学),西安710072

出　　处：《哈尔滨工业大学学报》2021年第6期48-53,共6页Journal of Harbin Institute of Technology

基　　金：国家自然科学基金(61573286)。

摘　　要：为探索增强小迎角下翼型气动性能的射流控制方法,进而实现无舵飞行控制,在环量控制的启发下,提出在NACA0012翼型下表面靠近后缘的位置布置射流(Jet on the lower surface of trailing edge,LSTE jet),并通过分析流动状态与参数变化优化LSTE射流的气动控制效果.首先,采用3套不同规模的网格对NACA0012翼型本身进行数值模拟,验证了数值模拟方法的收敛性与有效性.其次,通过比较流场的马赫数分布、流线和压力分布的变化,研究了LSTE射流影响翼型气动性能的机理.最后,研究了翼型的气动系数随射流的位置、动量系数和前向夹角的变化规律.结果表明:LSTE射流在后缘诱导产生逆时针的涡,形成低压分离区,使后缘主流向下偏折,增加了翼型的有效弯度,并且前缘的吸力峰也因此增加,从而增大了升力系数;LSTE射流越靠近后缘,动量系数越大,增升减阻效果越好,但翼型的失速迎角会减小1°~3°;在不同的迎角和射流动量系数下,翼型的最大升力和最小阻力可以同时在γ=60°~70°之间达到.利用LSTE射流可以有效改变小迎角下翼型的气动性能,对实现飞行器无舵操纵有一定意义.To explore a jet control method for enhancing the aerodynamic performance of airfoils at small angles of attack so as to realize rudderless flight control,inspired by circulation control,it was proposed to arrange the jet at the lower surface of the NACA0012 airfoil near the trailing edge,and optimize the aerodynamic control effect of(jet on the lower surface of trailing edge)LSTE jet by analyzing the flow states and parameter variations.Firstly,three sets of grids with different scales were used to simulate the NACA0012 airfoil,and the convergence and effectiveness of the numerical simulation method were verified.Secondly,the mechanism of the influence of LSTE jet on the aerodynamic performance of the airfoil was studied by comparing the changes in the distribution of Mach number,streamline,and pressure distribution of the flow field.Finally,the variations of the aerodynamic coefficients of the airfoil with the position,the momentum coefficient,and the forward angle of the jet were analyzed.Results show that LSTE jet induced a counterclockwise vortex at the trailing edge,forming a low-pressure separation zone,which deflected the main flow of the trailing edge and increased the effective camber of the airfoil,and the suction peak of the leading edge also increased,thereby increasing the lift coefficient.The closer the LSTE jet was to the trailing edge,the greater the momentum coefficient was,and the better the effect of lift increase and drag reduction was,but the angle of attack of the airfoil decreased by 1°to 3°.Under different angles of attack and jet flow coefficients,the maximum lift and minimum drag of the airfoil could be achieved betweenγ=60°-70°at the same time.LSTE jet can effectively change the aerodynamic performance of the airfoil at a low angle of attack,and has certain significance for the realization of aircraft rudderless control.

关 键 词：主动流动控制 定常射流 翼型 NACA0012 气动性能 LSTE射流 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]