基于欧拉方程的一种机翼气动弹性计算方法

An Aeroelastic Analysis Method of Wings Based on Euler Equations

利用一种双时间方法求解三维非定常欧拉方程,采用无限插值理论生成0-H型代数网格,考虑了机翼变形时的网格生成问题,通过与气动力方程的联立求解,在时间域内用二阶龙格一库塔方法求解机翼弹性运动方程。计算结果表明,本文计算方法具有较高的计算效率,所计算的颤振临界速度与风洞实验一致。

The wings of high-speed vehicles always encounter the aeroelastic problem. The traditional aeroelastic analysis methods (such as the famous NASTRAN) based on potential theory can only predict both aerodynamic and structural linear problems. However, The transonic flows, which are very important in aeroelasticity for high-speed vehicles, possess nonlinear characteristics. A numerical method based on Euler equations is presented to calculate the aeroelastic characteristics of wings in all subsonic, transonic and supersonic flows. The transfinite interpolation method is used to generate the grids around the wing, and a finite volume algorithm based on center difference is used to solve Euler equations. The dual-time scheme is introduced to treat the unsteady aerodynamic problem. The motion equations of elastic wing structure are marched by Runge-Kutta method in the time domain. Both static and dynamic deformations of the wings are considered. The numerical results are shown to be in good agreement with the aeroelastic experiments done by the authors as shown in Fig. 4.