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A second-order finite-difference scheme for computing three-dimensional supersonic flows of an ideal gas

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Publication:3199113
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DOI10.1016/0041-5553(89)90117-1zbMath0713.76074OpenAlexW1995212267MaRDI QIDQ3199113

M. K. Aukin, R. K. Tagirov

Publication date: 1989

Published in: USSR Computational Mathematics and Mathematical Physics (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1016/0041-5553(89)90117-1


zbMATH Keywords

inviscid gasconical flowssecond-order accurate schemesexplicit second-order accurate finite-difference schemesteady three- dimensional supersonic flows


Mathematics Subject Classification ID

Transonic flows (76H05) Finite difference methods applied to problems in fluid mechanics (76M20) Gas dynamics (general theory) (76N15)


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Optimal-contour design for a plane hypersonic engine output unit with account for the boundary layer, length, outer flow, and base end effects ⋮ Determination of the optimal contour of a supersonic jet engine outlet by the direct method ⋮ Calculation of base pressure and enthalpy behind a blunt trailing edge separating two supersonic streams with allowance for boundary layers and heat fluxes







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