基于修正面元法的机翼静气动弹性计算

计算物理 ›› 2014, Vol. 31 ›› Issue (1): 21-26.

基于修正面元法的机翼静气动弹性计算

贾欢, 孙秦, 刘杰

西北工业大学航空学院, 陕西西安 710072

收稿日期:2013-03-01 修回日期:2013-07-29 出版日期:2014-01-25 发布日期:2014-01-25
作者简介:欢(1987-),男,宁夏吴忠,博士生,主要从事飞机结构静气动弹性研究,E-mail:killerking.10ve@163.com
基金资助:
中航工业产学研创新项目(Cxy2010xG18)资助

A Corrected Panel Method for Static Aeroelasticity

JIA Huan, SUN Qin, LIU Jie

School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, China

Received:2013-03-01 Revised:2013-07-29 Online:2014-01-25 Published:2014-01-25

摘要/Abstract

摘要： 针对静气动弹性弱耦合解法多次迭代耗时较长的问题,提出一种斜率修正面元法计算气动力.该方法以机翼在不同迎角下的CFD数据作为修正基础,以直线段近似曲线段升力线,弥补面元法无法考虑非线性因素的缺陷.通过M6机翼气动力损失以及迎角补偿等静气动弹性的计算表明,相对于CFD技术,该方法保持了较高的准确度并且计算效率较高,适用于复杂结构优化.

关键词: 静气动弹性, 修正面元法, 气动力损失, 迎角补偿

Abstract: A corrected panel method is shown and applied to static aeroealsticity.Based on CFD data at different attack angles the method approximates curved lifting lines by linear segment.The corrected panel method fills drawback of original one by considering nonlinear factor.Compared with CFD,similar accuracy limit and higher efficiency are obtained in aerodynamic force loss and attack angle compensation of M6 wing.It indicates that the method is suitable for complex structure optimization.

Key words: static aeroealsticity, corrected panel method, aerodynamic force loss, attack angle compensation

中图分类号:

V215.3⁺2

贾欢, 孙秦, 刘杰. 基于修正面元法的机翼静气动弹性计算[J]. 计算物理, 2014, 31(1): 21-26.

JIA Huan, SUN Qin, LIU Jie. A Corrected Panel Method for Static Aeroelasticity[J]. CHINESE JOURNAL OF COMPUTATIONAL PHYSICS, 2014, 31(1): 21-26.