Possibilities for predicting steady boundary layer behavior are inferred from consideration of case of cone at angle of attack to supersonic stream; semi-infinite cone is useful idealization of nose portion of spike inlet or of nose portion of fuselage of supersonic aircraft or missile.


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    Title :

    Three-dimensional laminar boundary-layer flow


    Additional title:

    J Aeronautical Sciences


    Contributors:
    Moore, F.K. (author)


    Publication date :

    1953


    Size :

    10 pages


    Remarks:

    Bibliography


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :





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