Schlieren photographs were used in an investigation to determine the effects of changing the aspect ratio from infinity to 2 on the air flow past a wing at high subsonic Mach numbers. The results indicated that the decreased effects of compressibility on drag coefficients for the finite wing are produced by a reduction in the compression shock and flow separation.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Effects of Aspect Ratio on Air Flow at High Subsonic Mach Numbers


    Contributors:

    Publication date :

    1952-07-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English