关键词: 紊流边界层, 掺混方法, 力学模型, 可压, 激波, 翼型, 史密斯, 上表面, 计算结果, 微分方法

Abstract:

A new improved entrainment method for calculation of compressible turbulent boundary layer is suggested, in which the effect of non-equilibrium turbulent boundary layer on determining entrainment coefficient is taken into account, and a kind of lag-pressure gradient parameter is introduced into calculation of flow field with strong adverse pressure gradient, such as that near shock waves. For evaluation and validation of the method six numerical examples are presented, and the results show good agreement with experimental data. Moreover, in comparison with other threoretical methods the present method is as good as J. E. Green's method, T. Cebeci's method and Reynold's stress equation method, but more efficient in computation, and superior to P. I). Smith's method in approaching to the experimental data. The method is also extended to threedimensional cases.