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本文建立机翼-机身-平尾-立尾组合体跨音速纵向空气动力的混合差分线松弛迭代计算方案。在物理空间采用直角座标网格,列出组合体的远场边界条件,在流场内部和物面、涡面网格点上,满足速势方程,利用物面边界条件,将速势延拓到机身内部。做了两个算例,得到了收敛或接近收敛的结果,与实验尚符合。对收敛过程和超松弛加快收敛的方法作了一些研究,发现超音速点的松弛参数应取大于1。
In this paper, a hybrid iterative calculation scheme of slack-fuselage-tail-tail combined transonic longitudinal aerodynamic mixing differential line is established. The rectangular coordinate grid is used in the physical space to list the far-field boundary conditions of the composite body. The velocity field equations are satisfied on the internal and object-surface and vortex-mesh points in the flow field. By using the boundary conditions of the object surface, Expand to the inside of the fuselage. Two examples are given, and the result of convergence or near convergence is obtained, which is in good agreement with the experiment. Some researches have been done on the convergence process and the method of accelerating the over relaxation. It is found that the relaxation parameter of the supersonic point should be greater than 1.