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- W1590341417 abstract "Abstract : The development of a tool for solving the near field of a scramjet fuel injector was attacked by first developing a numerical technique for solving the laminar, supersonic near wake flow. It was considered important to develop a procedure that had a potential for reduced computation time compared with explicit methods. The implicit numerical procedure was extended to mixed subsonic/supersonic flow with shocks, expansions, and regions of reverse flow. In the present case, numerical results have been obtained for the laminar, supersonic near wake behind a rectangular base. This numerical method produced stable, convergent, and accurate solutions when applied to this complex flow problem." @default.
- W1590341417 created "2016-06-24" @default.
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- W1590341417 date "1978-01-01" @default.
- W1590341417 modified "2023-09-24" @default.
- W1590341417 title "An Implicit Finite Difference Procedure for the Laminar, Supersonic Base Flow." @default.
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