Wing tested with full span and partial span split flaps deflected 60° and without flaps; leading edge roughness tests made with flaps retracted configuration; some chordwise pressure distribution measurements made for all flap configurations of model.


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    Title :

    Effects of Mach number and Reynolds number on maximum lift coefficient of wing of NACA 230-series airfoil sections


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1947


    Size :

    14 pages


    Remarks:

    26 Supp plates, Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :