基于N-S方程的尾迹面法翼型气动阻力计算

刘周; 朱自强; 王晓璐; 吴宗成

基于N-S方程的尾迹面法翼型气动阻力计算

北京航空航天大学航空科学与工程学院, 北京 100083

基金项目: 国家自然科学基金资助项目(10472013); 航空科学基金资助项目(04A51044)

详细信息

中图分类号: V 211.3
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出版历程
- 收稿日期: 2005-04-07
- 网络出版日期: 2006-03-31

Wake integration method for airfoil drag evaluation using N-S equations

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

摘要

摘要: 研究了计算翼型阻力改进的方法——尾迹面法及尾迹面积分的位置和相应的积分技术.在亚跨声速时分别采用了表面积分和尾迹积分求得给定翼型RAE2822的阻力.结果显示,2种方法具有相同的结果,表明尾迹面积分方法是有效的,与实验值吻合较好.尾迹面法中,尾迹面位置应处于离后缘相对弦长距离0.6~1.0之间.尾迹面积分方法中积分结果不依赖于物体的详细几何外形,可以预计对曲率变化大的三维复杂外形,该方法有更大的优势.
- 尾迹面积分 /
- 表面积分 /
- 阻力计算 /
- N-S方程
Abstract: Minimal improved far field method for airfoil drag evaluation——wake integration method was introduced. The position of wake integration and associated integral technics were also discussed. Predicted drag values for a given airfoil(RAE2822 airfoil)were compared and discussed using the surface integration and wake integration methods under both subsonic and supercritical flow conditions. Numerical data show that the results of both methods are the same, which indicates the wake surface integration method is valid. The calculated values agree well with the experimental data. It also indicate that in the wake integration method, the location of wake integration surface should be set in the distance of 0.6~1.0 relative chord length from the trailing edge. In the mean time, the results of wake integration method is independent of the variation of detailed configuration surface. Wake integration method might be more potential for the complex three-dimensional configurations having large curvature variation on the surface compared with surface integration method.
- wake integration /
- surface integration /
- drag evaluation /
- N-S equations

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参考文献(1)

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