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中文摘要：
针对某中型民机在着陆构型下的抖振问题，进行了抖振边界（抖振始发攻角）的仿真预计。在生成流场计算网格时，采用非结构四面体网格划分，并用三棱柱网格对机翼表面的边界层进行局部细化，应用有限体积空间离散法和二阶LUSGS-τTs隐式时间推进法对基于雷诺平均的N-S方程（RANS）进行求解，选用SST二方程湍流模型来模拟湍流。根据N—S方程的定常计算结果，综合应用机翼表面流线、升力曲线斜率变化曲线、俯仰力矩斜率变化曲线这3种判据，对该飞机在着陆构型下机翼抖振的始发攻角进行了合理的预计分析。
英文摘要：
The buffet boundary （buffet onset） of a civil transport airplane wing with lantting configuration is predic- ted by numerical methods. In the generation of flow field mesh, unstructured tetralfedral mesh is used and the boundary layer on the wing surface is refined with prism mesh. Finite-volume scheme and two order LUSGS-Ts im- plicit scheme are applied to solve the three-dimensional Reynolds-Averaged Navier-Stokes （RANS） equations, SST Two-Equations turbulence model is employed to simulate the turbulent flows. By examining the results calculated with a steady Navier-Stokes equations solver of CFX, three kinds of buffet onset criteria： wing surface streamlines criterion, lift curve criterion and pitching moment curve criterion are adopted to synthetically predict the buffet on- set incidence.
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