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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。
Aiming at the chattering problem of a medium-sized civil aircraft under the landing configuration, the simulation prediction of the chattering boundary (the starting attack angle of chattering) is carried out. When generating flow field computing grids, the unstructured tetrahedron mesh was used and the boundary layer of the wing surface was partially refined by using the triangular prism grid. The finite volume spatial discretization method and the second order LUSGS-τTs implicit time Propulsion method is used to solve the Reynolds-averaged Navier-Stokes equations (RANS), and SST two-turbulence model is chosen to simulate turbulence. According to the steady-state calculation results of Navier-Stokes equations, three criteria of wing flow line, slope curve of lift curve and slope curve of pitching moment are comprehensively applied. A reasonable forecast is made.