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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    Title :

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


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 5 , n 5


    Publication date :

    1967


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :