Effects of nose bluntness, angle of attack, and boundary-layer cooling on boundary-layer transition on 8° half-angle cone are presented; small amount of bluntness was found to displace transition location rearward; greater amounts produced blunting transition reversal in that rearward movement of transition ceased and additional blunting produced forward displacement; maximum rearward displacement from cone tip was about 4.1 times that of sharp cone; data obtained are tabulated.


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    Titel :

    Shock tunnel investigation of boundary-layer transition at M = 5.5


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Stetson, K.F. (Autor:in) / Rushton, G.H. (Autor:in)

    Erschienen in:

    AIAA Journal ; 5 , n 5


    Erscheinungsdatum :

    1967


    Format / Umfang :

    8 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :