摘要
利用非结构运动网格技术,考虑三维机翼弹性变形求解三维跨音速非定常流场,同时耦合多自由度结构运动方程进行跨音速标模算例AGARD445.6机翼的颤振数值分析。采用的流动控制方程为三维非定常Euler方程。用中心有限体积法进行空间离散,用双时间隐式方法进行时间推进。数值分析获得的颤振临界速度与马赫数关系曲线明显反映了跨音速颤振临界速度随马赫数变化出现“凹坑”的物理特征。同时,数值分析结果与风洞实验结果一致性较好验证了所使用的方法。
The unstructured dynamic mesh technique is applied to simulate the flutter behaviour of the AGARD445.6 Wing. Full implicit dual-time temporal discretization and cell-center finite volume spatial discretization are adopted to solve the 3-D Unsteady Euler Equations. The structural equations of motion coupled with the governing flow equations are simultaneously time integrated by use of Rung-Kutta technique in time domain.Numerical results validate the physical characteristic of a typical transonic flutter 'dip'. Comparisons between numerical and experimental flutter characteristics show good agreement, giving confidence in the presented numerical technique.
出处
《振动与冲击》
EI
CSCD
北大核心
2005年第6期27-28,36,共3页
Journal of Vibration and Shock
