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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    Title :

    Investigation of crossflow shocks on delta wings in supersonic flow


    Additional title:

    Untersuchungen ueber stossartige Profilumstroemungen an Deltafluegeln bei Ueberschallstroemung


    Contributors:

    Published in:

    AIAA Journal ; 18 , 1 ; 85-93


    Publication date :

    1980


    Size :

    9 Seiten, 17 Bilder, 17 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English






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    Delta wings for supersonic transport

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