Measurements for range of Mach number up to 0.78; results showed that large increase in drag coefficient beyond critical Mach number indicated by wind tunnel tests was also obtained under flight conditions and that wake width was extended sharply when shock was encountered.


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    Title :

    Wake measurements behind wing section of fighter airplane in fast dives


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:
    Beeler, D.E. (author) / Gerard, G. (author)


    Publication date :

    1947


    Size :

    8 pages


    Remarks:

    10 Supp plates


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English