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.
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.
出处
《计算物理》
CSCD
北大核心
2014年第1期21-26,共6页
Chinese Journal of Computational Physics
基金
中航工业产学研创新项目(Cxy2010xG18)资助
关键词
静气动弹性
修正面元法
气动力损失
迎角补偿
static aeroealsticity
corrected panel method
aerodynamic force loss
attack angle compensation
