不同厚度翼型动态失速涡运动数值研究  

Numerical investigation of dynamic stall vortex movement of different-thickness airfoils

作　　者：王友进[1] 闫超[1] 周涛[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2006年第2期153-157,共5页Journal of Beijing University of Aeronautics and Astronautics

摘　　要：在低马赫数下,对三种不同相对厚度的NACA系列基本厚度翼型在俯仰振荡运动中的动态失速现象进行了数值研究.数值模拟时采用双时间法和LU-SGS隐式解法相结合的模式求解了非惯性坐标系下的非定常纳维-司托克斯(NS)方程组,空间离散采用Roe格式,并结合刚性动网格生成技术.采用全湍流计算,通过引入BL(Baldwin-Lomax)模型计入湍流影响.计算出的气动力迟滞曲线与实验结果变化趋势符合较好,表明了数值方法的有效性,同时通过比较和分析不同厚度翼型在轻失速和深失速下的流场结构,发现绕翼型的失速旋涡产生和发展规律是明显不同的.Dynamic stall of NACA airfoils of three kinds of different relative thickness undergoing pitching motion at low Mach number was numerically investigated. Dual time-step approach in conjunction with lower-upper symmetric-gauss-seidel（LU-SGS） implicit method were utilized to solve the unsteady navier-stokes （NS） equations in noninertial system, and Roe scheme was brought in for space discretization, incombined with stiff moving mesh generation technology. Fully turbulent solution was adopted, by using baldwin-lomax（BL） model. The computed load hysteresis loops indicate good agreement with the experiment results, which confirms that the numerical method is effective. Through comparing and analyzing different flow fields, it is simultaneously founded that the formation and development of stall vortex passing airfoil is obvious distinct for different-thickness airfoils during light stall and deep stall.

关 键 词：动态失速 分离涡 厚度 翼型 低速 

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]