In the study described, a finite difference approach to solving the rotational Euler equations, explicitly fitting shocks as a boundary, is applied to a variety of geometrical shapes in the lower supersonic Mach number regime. It is shown how special techniques based onthe physics of the flow can used to circumvent a variety of numerical difficulties encountered with the conical flow problem that are primarily associated with the initial value characteristics of the hyperbolic scheme, causing embedded shock-induced entropy and crossflow layers to develop on the body surface. (Jensen)


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    Titel :

    Investigation of crossflow shocks on delta wings in supersonic flow


    Weitere Titelangaben:

    Untersuchungen ueber stossartige Profilumstroemungen an Deltafluegeln bei Ueberschallstroemung


    Beteiligte:
    Siclari, M.J. (Autor:in)

    Erschienen in:

    AIAA Journal ; 18 , 1 ; 85-93


    Erscheinungsdatum :

    1980


    Format / Umfang :

    9 Seiten, 17 Bilder, 17 Quellen



    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch






    Nonlinear Supersonic Potential Flow over Delta Wings

    B. Grossman / M. J. Siclarit | AIAA | 1981


    Delta wings for supersonic transport

    Jones, Jr., J.L. / Hunton, L.W. / Gregory, T.J. et al. | Engineering Index Backfile | 1963