A new method for the design of shock-free supercritical airfoils, wings, and three-dimensional configurations is described. Results illustrating this procedure in two and three dimensions are given. They include modifications to part of the upper surface of an NACA 64A410 airfoil that will maintain shock-free flow over a range of Mach numbers for a fixed lift coefficient, and the modifications required on part of the upper surface of a swept wing with an NACA 64A410 root section to achieve shock-free flow. While the results are given for inviscid flow, the same procedure can be employed iteratively with a boundary-layer calculation in order to achieve shock-free viscous designs. With a shock-free pressure field, the boundary-layer calculation will be reliable and not complicated by the difficulties of shock wave, boundary-layer interaction. (Jensen)


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    Title :

    New method for designing shock-free transonic configurations


    Additional title:

    Eine neue Methode zum Entwurf von Bauteilen fuer schallnahe Geschwindigkeit mit stossfreiem Stroemungsverlauf


    Contributors:
    Sobieczky, H. (author) / Yu, N.J. (author) / Fung, K.Y. (author) / Seebass, A.R. (author)

    Published in:

    AIAA Journal ; 17 , 7 ; 722-729


    Publication date :

    1979


    Size :

    8 Seiten, 12 Bilder, 23 Quellen



    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English




    New Method for Designing Shock-Free Transonic Configurations

    H. Sobieczky / N. J. Yu / K-Y. Fung et al. | AIAA | 1979


    A new method for designing shock-free transonic configurations

    SOBIECZKY, H. / YU, N. / FUNG, K.-Y. et al. | AIAA | 1978



    Transonic Aircraft Configurations

    Panaras, Argyris G. | AIAA | 2012