Compilation of data obtained in flight with six pursuit type airplanes embodying typical conventional and low drag airfoils; these flight data, which cover range of Mach numbers from 0.15 to 0.72 and of Reynolds numbers from 4,400,000 to 19,500,000, are analyzed, together with pertinent model and airfoil data obtained in several wind tunnels.


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    Title :

    Effect of Mach and Reynolds numbers on maximum lift coefficient


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1946


    Size :

    20 pages


    Remarks:

    19 Supp Sheets, Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :