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- W2078126722 abstract "A scheme of computation is described which will allow the calculation of plane supersonic gas flow through ducts and around obstacles with an accuracy dependent mainly on the adequacy of the assumption that viscous and heat conductive effects may be confined to oblique shocks, these being represented by abrupt changes in flow variables. The computing scheme will keep track of an arbitrarily large number of discontinuities and will introduce those shocks, vortex sheets and midflow expansions which are necessary to represent discontinuity interactions. The methods used are applicable to the calculation of weak solutions of other hyperbolic systems." @default.
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- W2078126722 date "1968-10-01" @default.
- W2078126722 modified "2023-09-23" @default.
- W2078126722 title "The calculation of steady plane supersonic gas flows containing an arbitrarily large number of shocks" @default.
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- W2078126722 doi "https://doi.org/10.1016/0021-9991(68)90022-3" @default.
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