The first-order multidimensional flux difference splitting method (Parent, B., “Multidimensional Flux Difference Splitting Schemes,” AIAA Journal, Vol. 53, No. 7, 2015, pp. 1936–1948) is here extended to second-order accuracy through the use of limiters. The proposed second-order flux functions are such that they collapse to the first-order multidimensional flux difference splitting stencil in the vicinity of discontinuities and tend toward second-order finite difference stencils in smooth parts of the solution. Various test cases of interest to hypersonic flight including supersonic ramp injectors, shock-induced boundary-layer separation, and hypersonic viscous layers reveal that the proposed method achieves as much as a four times increase in resolution per dimension over its first-order counterpart or over the second-order symmetric total variation diminishing schemes. When integrated through a block-implicit approach, this entails as much as a 40-fold increase in computational efficiency while not compromising the symmetric total variation diminishing reliable convergence to steady-state, essentially monotone solution, and high resolution of boundary layers.


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    Titel :

    Multidimensional High-Resolution Schemes for Viscous Hypersonic Flows


    Beteiligte:

    Erschienen in:

    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :

    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik / 55.60 / 50.93 / 55.50 / 50.93 Weltraumforschung
    Lokalklassifikation TIB:    770/7040




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    Multigrid Techniques for Hypersonic Viscous Flows

    F. Grasso / M. Marini | AIAA | 1993


    High-Resolution Computations Of Hypersonic Flows

    Yee, H. C. / Klopfer, G. H. / Montague, J. L. | NTRS | 1991