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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    Title :

    Laminar heat transfer to spherically blunted cones at hypersonic conditions


    Additional title:

    AIAA J


    Contributors:

    Published in:

    AIAA Journal ; 2 , n 3


    Publication date :

    1964


    Size :

    7 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :