Solution for 2-dimensional flow of inviscid gas is obtained by numerical methods of analysis, divided into subsonic region analyzed by relaxation method of Southwell and supersonic region treated by method of characteristics; shapes of sonic line and shock wave are obtained by iteration techniques; distribution in flow pattern indicates interaction between subsonic and supersonic regions is negligible; comparisons with theoretical and experimental results.


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    Title :

    Numerical solution of flow of perfect gas over circular cylinder at infinite mach number


    Additional title:

    NASA -- Memo


    Contributors:


    Publication date :

    1959


    Size :

    33 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :


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