Heat-transfer distribution data obtained on 9° half-angle cone at Mach numbers near 20 and freestream Reynolds number between 8000 and 15,000/in. in hypervelocity tunnels are presented; test data are compared with L.Lees'laminar heat-transfer theory and shock-tunnel data on similar cones; good agreement between theory and data is obtained; experimental pressure and heat-transfer distributions were correlated over wide range of nose-bluntness ratios, cone half-angles, and Mach numbers by modifying correlation parameters proposed by H.K.Cheng.


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    Titel :

    Laminar heat transfer to spherically blunted cones at hypersonic conditions


    Weitere Titelangaben:

    AIAA J


    Beteiligte:
    Griffith, B.J. (Autor:in) / Lewis, C.H. (Autor:in)

    Erschienen in:

    AIAA Journal ; 2 , n 3


    Erscheinungsdatum :

    1964


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :