摘要
提出一种以当地流活塞理论和当地流小扰动线化理论分别计算大攻角翼面激波脱体流态的局部超音速区和局部亚音速区的非定常气动力,以时域积分方法求解颤振方程。改进大攻角翼面颤振分析的工程计算方法,并与风洞颤振试验结果进行了对比,计算精度满足工程设计要求。
An improved engineering approach to flutter analysis of wings with high angle of attack is presented. Unsteady aerodynamic force in supersonic and subsonic regions are calculated respectively with the local flow piston theory and the theory of local flow small disturbance linearization for a wing with high angle of attack and bow shock wave on its leading edge. And the flutter equations are solved by numerical integration in time domain. Numerical results are compared with wing-tunnel test results and it is shown that this approach is effective for engineering application.
出处
《振动与冲击》
EI
CSCD
北大核心
2007年第3期1-4,共4页
Journal of Vibration and Shock
关键词
颤振
大攻角
非定常气动力
颤振求解
flutter, high angle of attack, unsteady aerodynamic force, flutter analysis
