翼型失速颤振的基本性质研究

Based on the different numerical methods developed in present project, the fluid-structure interaction of elastic structure of any configurations (mainly for airfoils) moving in fluid is simulated and studied, especially for the airfoil with separated flow at high incidences. The effect of nonlinear aerodynamic force computed by viscous flow theory on the aeroelasticity is researched. The application of different numerical methods used in aeroelastic process simulation is checked. The effects of different parameters on aeroelasticity are studied. The developed numerical methods include:.(1).the unsteady Navier-Stokes equations for compressible flow are coupled with equations of elastic moving structure. The Navier-Stokes equations are solved based on the dual-time method and implicit LU algorithm for time marching. The finite volume scheme is used for discretization. A high-efficient grid generation method is introduced and improved. The equations of motion are solved by the well-known Runge-Kutta method.(2).The unsteady Navier-Stokes equations of incompressible flow is solved by discrete vortex method. Coupled with equations of motion, the aeroelastic process is simulated in the time domain..(3).The potential equation of incompressible flow is solved by linear panel vortex method. Coupled with equations of motion, the aeroelastic process is also simulated in the time domain. An aeroelastic wind-tunnel system is designed. The airfoil in the experiment system can be placed at different incidences. A lot of experimental data are obtained. The numerical results are in agreement with the experiments.

通过不同的数值模拟方法相互结合并通过风动实验研究翼型在不迎角有强分离流条件下固耦合问题的基本物理性质和规律,探索基本物理参数和流动状态与翼型振动性质之间的内在联?此工作对于认识航空航天领域中非线性气动弹性的实质和为实际应用提供指导计算工具有重要的学术意义和应用价值,还可以推广应用于桥梁及建筑等领域..