Final maximum lift coefficients for three airfoils tested with 0.20cw flap were about equal; increase in minimum profile drag coefficient with airfoil thickness was large, being about twice as great for NACA 23030 as for 23012 plain foil.


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    Title :

    Wind-tunnel investigation of N.A.C.A. 23012, 23021, and 23030 airfoils with various sizes of split flap


    Additional title:

    Nat Advisory Committee Aeronautics -- Report


    Contributors:


    Publication date :

    1939


    Size :

    13 pages


    Remarks:

    Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :