Results of measurements made during high speed wind tunnel tests presented for angles of attack ranging from 0.2 to 21.2° and for free stream Mach numbers ranging from 0.2 to about 0.7.


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    Title :

    Effect of compressibility on distribution of pressures over tapered wing of NACA 230-series airfoil sections


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1947


    Size :

    11 pages


    Remarks:

    24 Supp Sheets


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :