Euler flow solutions for transonic wind tunnel section

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    Abstract

    Steady, 2D Euler flow computations have been performed for a wind tunnel section, designed for research on transonic shock wave - boundary layer interaction. For the discretization of the steady Euler equations, an upwind finite volume technique has been applied. The solution method used is collective, symmetric point Gauss-Seidel relaxation, accelerated by nonlinear multigrid. Initial finest grid solutions have been obtained by nested iteration. Automatic grid adaptation has been applied for obtaining sharp shocks. An indication is given of the mathematical quality of four different boundary conditions for the outlet flow. Two transonic flow solutions with shock are presented; a choked and a non-choked flow. Both flow solutions show a good shock capturing. A comparison is made with results obtained by holographic interferometry. Keywords: steady Euler equations - transonic flows - mutigrid methods - grid generation and adaptation - boundary conditions
    Original languageEnglish
    Title of host publicationPapers Presented at the V. Aerodynamic Seminar of Lehrgebiet Aerodynamik Des Fluges, Technical University Aachen (RWTH) on July (5 - 7), 1987
    EditorsA. Nastase
    Place of PublicationHanau
    PublisherHaag + Herchen
    Pages14-26
    ISBN (Print)9783925714320
    Publication statusPublished - 1990

    Publication series

    NameProceedings of High Speed Aerodynamics
    VolumeII

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