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提出了一种新的利用表面流函数法计算高超声速飞行器表面流线分布的方法.首先提出了表面流函数的概念,并通过理论推导,得到了表面流函数与表面流线的关系;然后运用结构化网格求解三维Eu-ler方程,计算得到高超声速钝头体的边界层外缘外部无粘流场气流参数;最后利用无粘流场气流参数和表面流函数的方法计算了高超声速飞行器的精确表面流线分布.结果表明,在无攻角和攻角小于20°的情况下均可以得到较好的壁面流线分布.高精度的表面流线的得到,为利用边界层内粘性主导区域的积分方程等方法进一步精确预测高超声速飞行器表面的气动加热奠定了基础.
A new method to calculate the streamline distribution on the surface of hypersonic vehicles by using the surface flow function method is proposed.Firstly, the concept of surface flow function is proposed and the relationship between surface flow function and surface flowline is obtained through theoretical derivation. Structured Eulerian equation was solved by a structured grid to calculate the external viscous flow parameters of the outer boundary layer of the hypersonic blunt body. Finally, by using the flow parameters of the non-viscous flow field and the surface flow function, the hypersonic vehicle The results show that the wall flow distribution can be obtained well at angles of attack and angles of attack less than 20 °, and the high-precision surface flow line is obtained by utilizing the viscous dominance in the boundary layer Regional integral equation and other methods to further accurately predict the aerodynamic heating of the surface of the hypersonic vehicle laid the foundation.