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The supersonic and hypersonic.laminar and turbulent vi-scous separated flows over two and three-dimensional com-pression corners are solved by the antidissipative explicit-implicit difference scheme presented in this paper.The re-sults obtained show that a high accuracy has been achieved bythis method and the time needed for computation is greatlyreduced.
The supersonic and hypersonic.laminar and turbulent vi-scous separated flows over two and three-dimensional com-pression corners are solved by the antidissipative explicit-implicit difference scheme presented in this paper. The re-sults obtained show that a high accuracy has been achieved bythis method and the time needed for computation is greatlyreduced.