二维机翼振动非定常流场的数值模拟  

Numerical simulation of the unsteady flow field around a two-dimensional oscillating airfoil

作　　者：金琰[1] 袁新[1] 

机构地区：[1]清华大学热能工程系,北京100084

出　　处：《清华大学学报（自然科学版）》2002年第5期684-687,共4页Journal of Tsinghua University(Science and Technology)

基　　金：国家"九七三"基础研究项目 ( G19990 2 2 30 4);国家自然科学基金资助项目 ( 5 0 0 76 0 19)

摘　　要：准确数值模拟机翼动态失速时非定常流场主要有湍流模型和数值算法两方面的难点。在研究湍流模型的基础上 ,采用了 q-ω低 Reynolds数双方程湍流模型 ,并采用了一种高精度、高分辨率的数值计算方法 (L U- SGS- GE隐式算法和四阶 MUSCL TVD格式 )数值模拟了振动机翼周围的附着流动、轻度失速和深度失速非定常流场。结果表明 :采用本方法计算附着流动和轻微失速状态流场时 ,其升力系数迟滞曲线和阻力系数迟滞曲线与实验结果吻合得令人满意。The numerical simulation of the unsteady flow field around an oscillating airfoil is difficult because of the complexity of turbulence models and numerical methods. After a detailed study of various turbulent flow models, the authors used a q-ω low-Reynolds double-equation turbulence model and a high-accuracy higher-order numerical method (the LU-SGS-GE implicit method and the fourth-order MUSCL TVD scheme) to analyze the attached flow, light stall and deep stall of an oscillating airfoil. For the attached flow field and the flow field during a slight stall, the calculated hysteresis curves of the lift and the drag factors agree well with test results. The calculated results for a deep stall are much more accurate than previously reported results.

关 键 词：振动机翼 非定常流场 湍流模型 数值模拟 升力系数 阻力系数 二维流场 深度失速 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]