The effectiveness of a new version of an elliptic cross-section tip in controlling the asymmetry of the vortex wake of an axisymmetric body at angle of attack has been studied. The elliptic cross sections were generated using two sixth-degree polynomials such that the tip radius, slope, and curvature would match those of a right circular cone at the point where the polynomial became tangent to a cone generator. The tip was found to be effective in varying the vortex wake geometry of a right circular cone at large angle of attack. The measured side force coefficient varied smoothly with tip roll angle for the two lowest angles of attack studied and exhibited square-wave and more undesirable variations for the larger angles of attack studied. These square-wave and peak, reduction-in-magnitude, and change-in-sign variations were caused by vortex breakaway, which allowed vortex crossover to occur. Ahead of vortex breakdaway, the elliptic cross-section tip yielded smooth variations of vortex wake asymmetry with tip roll angle, indicating that the tip would possibly be a feasible control device for high-performance fighter aircraft at high angle of attack.


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    Titel :

    Elliptic tip effects on the vortex wake of an axisymmetric body at incidence


    Weitere Titelangaben:

    Auswirkungen der konischen Flugzeugnase mit elliptischem Querschnitt auf die Wirbelnachströmung eines angestellten achsensymmetrischen Flugkörpers


    Beteiligte:
    Bridges, D.H. (Autor:in) / Hornung, H.G. (Autor:in)

    Erschienen in:

    AIAA Journal ; 32 , 7 ; 1437-1445


    Erscheinungsdatum :

    1994


    Format / Umfang :

    9 Seiten, 16 Bilder, 29 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch