Free-flight dynamic stability measurements of 10° half-angle cones with laminar and "tripped" boundary layers at supersonic speeds are presented and effects of Mach number, center-of-gravity position, and angle-of-attack oscillatory amplitude on dynamic stability are also shown; free-flight results show that dynamic stability is not perceptibly affected by state of boundary layer but is affected by amplitude of oscillation; data are compared with M.Tobak's potential flow solution and solution using Newtonian impact theory at all angles of attack.


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    Titel :

    Effect of boundary-layer transition on dynamic stability


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Jaffe, P. (Autor:in) / Prislin, R.H. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :


    Effect of boundary-layer transition on dynamic stability.

    Jaffe, P. / Prislin, R. H. | NTRS | 1966


    Effect of boundary-layer transition on dynamic stability.

    JAFFE, P. / PRISLIN, R. H. | AIAA | 1966



    Effect of nose bluntness on boundary layer stability and transition

    MALIK, M. / SPALL, R. / CHANG, C.-L. | AIAA | 1990


    Three-Dimensional Boundary Layer Stability and Transition

    Li, F. / Malik, M. R. | SAE Technical Papers | 1992