This paper contains a tabulation of functions of the Mach number which are frequently used in high-speed aerodynamics. The tables extend from M = 0 to M = 10.0 in increments of 0.01 and are based on the assumption that air is a perfect gas having a specific heat ratio of 1.400.


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    Title :

    Compressible Flow Tables for Air


    Contributors:

    Publication date :

    1947-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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