摘要
本文利用大攻角带分离流机翼的完全非定常非线性气动力计算方法,通过与机翼运动方程的同时求解,在时间域内实现了大攻角机翼非线性气动弹性的数值模拟,根据弹性机翼各种状态下的运动过程,可以得到大攻角机翼的颤振速度等重要参数以及亚临界、超临界等飞行状态的运动规律。算例结果表明,大攻角下机翼的气动弹性问题需引起足够的重视。
In this paper, a numerical method is presented for predicting the static and dynamic aeroelastic characteristics of wings with separation at large angle of attack. The numerical method is used to give the nonlinear aerodynamic loads of wings at large angle of attack in subsonic flow. In the time domain, the governing structural equations of the system are solved by numerical method. The varying process of wing vibration can be plotted versus the time at different velocity. As an example, a rectangular wing with side edge separation is considered. The calculated results are compared with those obtained under linear airloads. It is shown by the numerical results that the nonlinear aeroelastic characteristics of wings with sharp edge separations at large angle of attack must be taken into account in aircraft design.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1990年第1期A031-A036,共6页
Acta Aeronautica et Astronautica Sinica
关键词
大攻角
机翼
气动弹性
数值计算
wings at large angle of attack, nonlinear, aeroelasti-city, numerical method.
