一种基于连续核函数展开的跨声速气动力修正法

计算物理 ›› 2015, Vol. 32 ›› Issue (4): 416-422.

一种基于连续核函数展开的跨声速气动力修正法

刘祥, 孙秦, 武亮

西北工业大学航空学院, 陕西西安 710072

收稿日期:2014-07-15 修回日期:2014-12-01 出版日期:2015-07-25 发布日期:2015-07-25
作者简介:刘祥(1991-),男,博士,主要从事飞机结构及气动弹性研究,E-mail:liuxiang090209@163.com
基金资助:
中航工业产学研创新项目(Cxy2010xG18)资助

A Transonic Aerodynamics Correction Method with Successive Kernel Expansion

LIU Xiang, SUN Qin, WU Liang

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

Received:2014-07-15 Revised:2014-12-01 Online:2015-07-25 Published:2015-07-25

摘要/Abstract

摘要： 现有的跨声速修正面元目的大多难以准确修正非定常压强系数的虚部.结合下洗修正目的和连续核函数展开法(Successive Kernel Expansion Method),发展了一种新的修正目的.计算ONERA M6机翼的非定常气动力,与传统修正目的比较,结果表明该目的具有更高的精度.将改进的非定常气动力用于机翼的跨声速颤振分析,较好地预测了机翼在跨声速区域的非线性颤振特性.

关键词: 修正面元法, 连续核函数展开, 非定常气动力, 颤振边界

Abstract: Most of current corrected panel methods failed to correct out-of-phase part of distributed unsteady pressure. A method combining traditional downwash weighting method and successive kernel expansion is developed. Precision of the method is verified with an example on ONERA M6 wing. Based on modified aerodynamics,flutter boundary of wing is calculated which predicts well nonlinear flutter of wing in transonic regime.

Key words: corrected panel method, successive kernel expansion method, unsteady aerodynamics, flutter boundary

中图分类号:

V2153

刘祥, 孙秦, 武亮. 一种基于连续核函数展开的跨声速气动力修正法[J]. 计算物理, 2015, 32(4): 416-422.

LIU Xiang, SUN Qin, WU Liang. A Transonic Aerodynamics Correction Method with Successive Kernel Expansion[J]. CHINESE JOURNAL OF COMPUTATIONAL PHYSICS, 2015, 32(4): 416-422.