Paper is concerned with hypersonic flow over flat plate with blunt nose; analysis is based on flow model in which flow field behind shock wave may be divided into inviscid hypersonic flow region and entropy layer, across which pressure has no appreciable change; validity of assumptions made is examined from numerical results, and region of validity found to extend over large range of nondimensional distance from leading edge.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Blunt-leading-edge problem in hypersonic flow


    Additional title:

    AIAA J


    Contributors:
    Oguchi, H. (author)

    Published in:

    AIAA Journal ; 1 , n 2


    Publication date :

    1963


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :