摘要
采用流固耦合的数值计算方法研究了NACA 0 0 15翼型在大迎角 ( 15°～ 6 0°)范围的颤振 ,以及在翼型背部部分引入射流的减振技术。在流体区域用高精度、高分辨率算法求解Farve平均的Navier Stokes方程 ,在固体区域用四阶Runge Kutta法求解振动方程 ,并且每一个时间步后都在两个区域之间传递边界条件。计算结果表明在翼型背部引入适当射流会降低翼型的振动 ,并提高升力。但如果引入射流的速度过高 ,会在叶背处形成新的分离流 。
Fluid-structure coupling numerical method is used to analyze NACA 0015 airfoil's flutter and flutter control technique of blowing at large incidence angles (15-60 degrees). A higher-order, high resolution MUSCL TVD scheme has been used to solve the Farve-averaged Navier-Stokes equations in the fluid zone. Fourth-order Runge-Kutta method has used to solve the oscillation equations in the solid zone. Boundary conditions are transferred between the two zones after each time-step. The numerical results show that the appropriate blowing will reduce the oscillation amplitude and increase the lift coefficient. But surplus blowing will create new vortical structures near the airfoil, which causes the lift coefficient to drop.
出处
《空气动力学学报》
EI
CSCD
北大核心
2002年第3期267-273,共7页
Acta Aerodynamica Sinica
基金
国家重点基础研究专项经费资助 (No .G19990 2 2 3 0 6)
国家自然科学基金资助 (No .5 0 0 760 19)
关键词
流固耦合
数值方法
机翼
射流
减振技术
飞机
NACA 0015 airfoil
fluid-structure coupling
aeroelasticity
flutter
blowing
separated flow
