Particle-in-cell method was used to obtain numerically full, time-dependent development of plane or cylindrical wake behind flat base of projectile moving with supersonic speed through air; particular attention is paid to case of Mach 1.89, arising from passage of very strong shock over projectile at rest; many features are shown of transient build-up to statistically steady state, as well as of late-time flow behavior.


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    Title :

    Numerical calculation of supersonic wake flow


    Additional title:

    AIAA J


    Contributors:
    Amsden, A.A. (author) / Harlow, F.H. (author)

    Published in:

    AIAA Journal ; 3 , n 11


    Publication date :

    1965


    Size :

    15 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    Numerical calculation of supersonic wake flow.

    AMSDEN, A. A. / HARLOW, F. H. | AIAA | 1965


    Supersonic wake flow visualization

    HALL, C. R. / MUELLER, T. J. / SULE, W. P. | AIAA | 1969


    Supersonic wake flow visualization

    HALL, JR., C. / MUELLER, T. / SULE, W. | AIAA | 1969