摘要
现有的跨声速修正面元方法大多难以准确修正非定常压强系数的虚部.结合下洗修正方法和连续核函数展开法(Successive Kernel Expansion Method),发展了一种新的修正方法.计算ONERA M6机翼的非定常气动力,与传统修正方法比较,结果表明该方法具有更高的精度.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.
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.
出处
《计算物理》
CSCD
北大核心
2015年第4期416-422,共7页
Chinese Journal of Computational Physics
基金
中航工业产学研创新项目(Cxy2010x G18)资助
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
corrected panel method
successive kernel expansion method
unsteady aerodynamics
flutter boundary
