针对长宽比为0.5的试验壁板模型,采用Menter's SST两方程湍流模型,通过CFD/CSD耦合实现超声速及高超声速壁板颤振的时域计算,来研究湍流边界层厚度对颤振动压的影响.分别计算了不同马赫数下不同边界层厚度的颤振动压.结果表明,边界层厚度在低超声速阶段对颤振动压影响显著.在马赫数为1.2时边界层影响达到最大,其结果超过无粘结果160％,计算结果和试验值吻合良好.随着马赫数增加湍流边界层影响很快降低,但仍有较大影响,在马赫数为8.0时颤振动压比无粘结果高20％.因此,要更精确计算高超声速流动中的壁板颤振,湍流边界层效应是必须考虑的因素.%In this paper, a tight coupled CFD/CSD method is used to solve supersonic and hypersonic panel flutter problem in time domain for a test flat panel model with aspect ratio of 0. 5. The Menter's SST two-equation turbulent model is employed for simulating viscous effects. Flutter dynamic pressure is calculated under different boundary layer thickness and Mach number; the results show that the boundary layer thickness has a large stabilizing influence on the flutter of flat panels. The effect on flutter dynamic pressure is at the maximum near Ma=1. 2 and then is decreased rapidly with increasing Mach number, which agrees well with experimental data. The dynamic pressure is 20% higher than the Euler results at Ma= 8, the influence of turbulent boundary layer thickness can not be neglected at hypersonic flow. The turbulent boundary layer play a dumping effect most hypersonic case, and it must be taken into account to achieve more accurate result of panel flutter in hypersonic flow.
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