Experiments were conducted in supersonic wind tunnel at Jet Propulsion Laboratory of California Institute of Technology on effect of heat transfer (cooling) on size of single spherical roughness elements required to produce minimum transition Reynolds number on 43-in. 10° cone; results are extension of previous work on adiabatic cone, indexed in Engineering Index 1962 p 9-10; dependence of roughness size on trip position, Mach number, and surface temperature is expressed in simple relation.


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    Title :

    Boundary-layer transition at supersonic speeds -- Roughness effects with heat transfer


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 6 , n 4


    Publication date :

    1968


    Size :

    5 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :