This article presents a new methodology for the construction of outlet boundary conditions for the numerical simulation of supersonic flows whose velocity component normal to the boundary remains subsonic. The methodology is based upon the full non-linear system of equations for steady two-dimensional supersonic irrotational flows. It allows the correct flow pattern recognition independently of the location of the outlet boundary for both smooth and discontinuous flow fields. It is presented within the context of high pressure ratio nozzle vanes and supersonic compressor cascades. Comparisons with both analytical solutions and experimental results have demonstrated the correctness of the proposed approach for very short computational domains.
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