关键词: 大攻角机翼, 非线性, 气动弹性, 数值计算

Abstract: 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.

Key words: wings at large angle of attack, nonlinear, aeroelasticity, numerical method