Results presented of drag tests of six bodies of revolution with systematically varying shapes and with fineness ratio of 5; forms were derived from source-sink distributions and formulas presented for calculation of pressure distributions of forms; tests made in NACA variable density wind tunnel.


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    Title :

    Fuselage-drag tests in variable-density wind tunnel: streamline bodies of revolution, fineness ratio of 5


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1937


    Size :

    11 pages


    Remarks:

    5 Supp sheets, Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English