基于修正面元法的机翼焦点位置变化研究

针对静气动弹性问题中机翼焦点位置求解精度与效率的矛盾,提出采用分段斜率修正面元法来计算气动力,该方法以刚体机翼在不同迎角下的CFD数据作为修正基础,对弹性变形后的机翼下洗采用分段修正,克服了传统面元法无法考虑非线性因素的缺点。通过M6机翼气动焦点位置的计算表明:相对于CFD方法,该方法保持了较高的准确度并且计算效率较高;相对于传统面元法,该方法能够准确地计算焦点位置和弹性机翼焦点位置变化量,适用于工程设计。

The research of aerodynamic center location based on a correction panel method

A correction panel method was presented and applied to calculate the aerodynamic center location which is an important parameter in static aeroelasticity problem. The method which based on the CFD data at different attack angle corrected the downwash of the elastic deformation sectionally. Correction panel method fills the drawback of the panel method by including the nonlinear factor. Taken m6 wing aerodynamic center calculation as examples, this method keep high accuracy as well as CFD but performance higher efficiency. The method can get the aerodynamic center location and the aerodynamic center location changes correctly which the traditional panel method cannot handle. This slope corrected method is suitable for design stage of structure project.