摘要
通过对移动壁面的作用原理进行分析,建立了一类可用于移动壁面模拟的广义滑移壁面模型,依此建立了移动壁面的准定常数值模拟方法。数值研究了移动壁面对来流速度为40 m/s的低速NACA0015翼型在临界攻角状态(11°)气动性能影响,其中,移动壁面机构为放置在翼型前缘和背风面的两个转动圆柱。计算研究结果表明,在临界攻角状态,移动壁面对翼型气动性能产生显著的主动和被动控制效果,即:通过显性引入移动壁面,将使基本翼型在临界状态的气动性能变差,但通过移动壁面的运动,并采用恰当的控制策略,将对气动性能产生明显的补偿,抑制边界层的发展,延缓分离;控制圆柱的安装位置、转动方向及转动速率是影响流动控制效果的关键因素。
A quasi- steady method for numerical simulation of moving surface is proposed based on a new slip wall boundary condition model, and is used for numerical study on aerodynamics characteristics of NACA0015 airfoil with moving surface near the critical angle of attack, in which tow rotating cylinders are installed at the leading edge and the leeward side of the airfoil separately. The computational results show that the moving surfaces can work well as a passive flow control device as well as the active one to take obvious effect on aerodynamic characteristics of the airfoil. It is found that the performance of the airfoil would get worse with the installation of local moving surfaces devices; nevertheless, its performance can be compensated with rotation of the moving surface and based on a reasonable flow control strategy such that the boundary layer of airfoil is suppressed, and the separation is delayed. It is also shown that, when using moving surface as flow control devices, the installation of the rotating cylinders, the rotating direction, and the rotating speed are the most important factors that affect the effect for flow control.
出处
《航空计算技术》
2015年第4期18-20,28,共4页
Aeronautical Computing Technique
基金
国家863计划项目资助(2012AA01A304)
中欧航空科技合作专项项目资助(FP7/2010-266326)
