翼型厚度对气动弹性特性的影响

结合基于$k$-$\omega$的SST两方程湍流模型，求解雷诺平 均Navier-Stokes方程获得定常和非定常气动力，耦合翼型弹性运动方程，在时间 域内模拟了不同厚度对称翼型在不同迎角下的气动弹性动态过程， 并重点研究了较大迎角下的不同厚度翼型流场特征和气动弹性的性质，研究结果表明：在论 文所涉及的参数情况下，对于迎角从零到大迎角范围，翼型颤振临界速度随迎角的变化不是 单调的. 翼型颤振临界速度迅速下降的起始迎角比最大升力系数对应的迎角小很多.

THE EFFECTS OF AIRFOIL THICKNESS ON AEROELASTIC CHARACTERISTICS

Based on the Reynolds-Averaged Navier-Stokes equations and $k$-$\omega $ SST turbulent models, the steady and unsteady flows are computed. Coupled with the motion equations for an elastic supported airfoil, the aeroelastic dynamic responses of the symmetric airfoil with different thicknesses at different incidences are simulated in the time domain. The flow-field characteristics and the aeroelastic characteristics of airfoil with different thicknesses at high-incidence are investigated. It is shown that, the critical flutter speed does not vary monotonously with the incidence increasing from zero to high levels for various Reynolds numbers and structure parameters considered in this paper. The incidence at which the critical flutter speed begins to drop rapidly is much smaller than the incidence corresponding to the maximum lift coefficient.