Transition characteristics were determined for smooth, blunt nosed cones varying from 27 to 60° in included angle; Mach number effects were small for small bluntnesses but increased for larger; strongest effect was in Mach number range 1.61 to 1.82; increase in nose bluntness caused decrease in transition distance and transition Reynolds number.


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    Title :

    Effects of cone angle, Mach number, and nose blunting on transition at supersonic speeds


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    31 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :




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