Abstract
Recently, a solution adaptive Chimera grid scheme applying the structured Adaptive Mesh Refinement (AMR) algorithm has been developed by the authors for simulating multiple and moving body supersonic flows. Two CFD methodologies, the Chimera grid method and the AMR algorithm were integrated. A complex multiple and moving body configuration can be easily meshed by the Chimera grid method, and each domain of the initial coarse Chimera grid system is then adapted by the AMR algorithm according to the flow solution. The advantages of the Chimera grid method and the AMR algorithm are combined. In this paper, numerical solutions of a shock interaction with an aerofoil, together with the subsequent interaction of a vortex generated at the trailing edge of the aerofoil interacting with a further aerofoil are presented. The results are obtained from this new solution adaptive Chimera grid scheme (AMRC code) and are analysed and compared with both experiment and previous computational results. The simulations demonstrate the flexibility of grid generation and the high efficiency and the ability to resolve and track complex flow features
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