不同厚度翼型动态失速涡运动数值研究

王友进; 闫超; 周涛

不同厚度翼型动态失速涡运动数值研究

北京航空航天大学航空科学与工程学院, 北京 100083

详细信息

作者简介:
王友进(1980-),男,湖北枝江人,硕士生, wyj1980@sohu.com.

中图分类号: V 211.3
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- 被引次数: 0
出版历程
- 收稿日期: 2004-11-30
- 网络出版日期: 2006-02-28

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

School of Aeronautic Science and Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

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.
- 动态失速 /
- 分离涡 /
- 厚度 /
- 翼型 /
- 低速
Abstract: 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.
- dynamic stall /
- separation vortex /
- thickness /
- airfoil /
- low speed

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参考文献(1)

[1] 白鹏,崔尔杰,周伟江,等. 等速上仰翼型动态失速现象的研究[J] 力学学报,2004,36(5):569~576 Bai Peng, Cui Erjie, Zhou Weijiang, et al. Investigation of the dynamic stall about the pitching airfoil[J] Acta Mechanica Sinica, 2004, 36(5):569~576(in Chinese) [2] Ekaterinaris John A, Platzer Max F. Computational prediction of airfoil dynamic stall[J] Aerospace Sci,1997,33:759~846 [3] McCroskey W J. The phenomenon of dynamic stall . NASA TM-81264, 1981 [4] 周瑞兴,上官云信,解亚军,等. 两种厚度翼型动态失速特性的研究[J] 西北工业大学学报,1999,17(3):475~479 Zhou Ruixing, Shangguan Yunxin, Xie Yajun, et al. Dynamic stall characteristics of two different rotor-blade airfoils[J] Journal of Northwestern Polytechnical University, 1999,17(3):475~479(in Chinese) [5] Martin P B, Tung C. Compressible dynamic stall control using a variable droop leading edge airfoil [J] Journal of Aircraft, 2004, 41(4):862~869 [6] 袁先旭. 非定常流动数值模拟及飞行器动态特性飞行研究 . 绵阳:中国空气动力研究与发展中心,2002 Yuan Xianxu. Numerical simulation for unsteady flows and research on dynamic characteristics of vehicle .Mianyang:China Aerodynamics Research and Development Center, 2002(in Chinese) [7] Pulliam T H, Steger J L. Recent improvements in efficiency, accuracy, and convergence for implicit approximate factorization algorithms . AIAA 85-0360, 1985 [8] Clarkson J D , Ekaterinaris J A , Platzer M F. Computational investigation of airfoil stall flutter . In:Atassi H M, ed. Unsteady Aerodynamics, Aeroacoustics and Aeroelasicity of Turbomachines and Propellers . Berlin:Springer, 1993. 415~432 [9] Wu J C, Sankar N L. Evaluation of three turbulence models for the prediction of steady and unsteady airloads . AIAA 89-0609,1989

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