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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    Title :

    Effect of boundary-layer transition on dynamic stability


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Jaffe, P. (author) / Prislin, R.H. (author)

    Published in:

    Publication date :

    1966


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    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



    Three-Dimensional Boundary Layer Stability and Transition

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


    Three-Dimensional Boundary Layer Stability and Transition

    Malik, M. R. / Li, F. / SAE | British Library Conference Proceedings | 1992