摘要
使用全耦合法预测了翼型NLR7301的颤振边界。在流体域的动网格上,通过求解非定常的雷诺平均N-S方程,计算出翼型表面的非定常气动力。在耦合了翼型的结构动力学方程后,得到翼型表面的变形位移,通过变形网格技术对流体域的网格进行更新。在此基础上利用时间推进的方法模拟了翼型的自激振动过程。
A fluid/structure coupled method is developed to predict the flutter boundary of NLR7301 airfoil. In the aerodynamics domain, the time-dependant aerodynamic force on the surface of the airfoil is computed by solving the unsteady Reynolds averaged Navier-Stokes equation. Coupled with a structure dynamics equation of the airfoil, the surface displacement of the airfoil is computed. With a dynamic mesh-deformation technique, the interior nodes of the CFD grid is moved accordingly in order to reflect the motion of the airfoil surface, thus the time history of the airfoil self-excited vibration is simulated.
出处
《科学技术与工程》
2010年第19期4704-4708,共5页
Science Technology and Engineering
