X—38飞行器无粘绕流的非结构网格模拟

本文采用非结构网格，利用DLR所发展的计算软件TAU对X－38飞行器高超声速无粘绕流进行数值计算。为了生成有效的计算网格及提高对流场细节的分辨率，在求解过程中应用了网格自适应,并研究了网格密度对气动力的影响程度；同时与现有的实验结果和用结构网格得到的结果进行了比较，符合程度令人满意。

Hypersonic inviscid flow computation over X-38 with unstructured meshes

The DLR code TAU is applied to the computation for X-38, with the unstructured grids produced by unstructured mesh generation system CENTAUR. In the solver AUSMDV is adopted. The solution is advanced in time by 3 stage Rugge Kutta time stepping scheme with convergence accele rated to steady state by local time stepping. An adaptation method is used in this work in order to produce efficient grids and to get accurate results. Meanwhile, the effects of grid density on aerodynamic forces is investigated. The solutions resulting from the TAU code are compared with the wind tunnel data and structured results obtained by another DLR code. The results indicate that the agreements are rather good.