摘要
基于偶极子网格法的面元法难于考虑机翼厚度、迎角以及粘性等效应,且不能处理受激波影响的跨声速非线性气动力等问题。通过分析传统面元修正方法在非定常气动力计算方面的不足,采用核函数展开法进行非定常气动力系数修正。针对M6机翼实例进行了特定结构模态下的跨声速非定常气动力研究,结果表明:核函数展开法能够解决面元法对复杂流态计算精度偏低的问题,对于非定常气动力计算效率具有学术研究和工程应用价值。
The effects of thickness,angle of attack and viscosity on aerodynamics are not concerned in panel method based on doublet vortices method deeply. Moreover,it can＇t deal with nonlinear aerodynamics effected by shock wave. The Successive Kernel Expansion Method（ SKEM） is used to correct unsteady aerodynamic pressure coefficient by analysis of traditional panel correction methods＇ deficiencies on calculation of unsteady aerodynamics. A conclusion can be drawn from the study of transonic unsteady aerodynamics of a M6 wing under a specific structural mode that the SKEM is able to improve the low accuracy of panel method under complex fluids,which has a great value and significance in academic study and engineering application on calculation efficiency of unsteady aerodynamics.
出处
《航空计算技术》
2015年第6期83-86,共4页
Aeronautical Computing Technique
关键词
非定常气动力
偶极子网格法
气动力系数修正
核函数展开法
unsteady aerodynamics
doublet lattice method
correction of aerodynamic pressure coeffi cient
successive kernel expansion method
