CONSERVATIVE OVERLAPPING GRID GENERATION IN SUPERSONIC VISCOUS FLOW OVER COMPLEX GEOMETRY

摘要

In this paper, a three-dimensional conservative interface algorithm of overlapping grids in simulating supersonic flow about complex geometry is presented. The conservative algorithm contains the conservative interpolation and characteristics decomposition of numerical flux. Based on the algorithm, a procedure, COGRID, has been developed and a three-dimensional implicit flow solver with second-order TVD algorithm is developed to predicate the flow field. To verify the conservative interface algorithm, the case of supersonic flow around a cylinder is tackled. Application of the conservative algorithm in simulating flow about complex geometry is validated by computations of a case of the wing-body combination. Results show that with the conservative algorithm, a good agreement can be obtained by comparisons with the experimental data, and the conservative algorithm possess better capability in predicating the complex flow field than a non-conservative algorithm.