Tests of 10 by 60 in Clark Y main airfoil and NACA 0012 flap having chord equal to 15% of main wing chord; axis of flap in all cases was on flap chord and 20% back from its leading edge; no serious adverse change in lateral stability was found to result from use of flap in optimum position.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Wind-tunnel tests of wing with trailing-edge auxiliary airfoil used as flap


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Notes


    Contributors:
    Noyes, R.W. (author)


    Publication date :

    1935


    Size :

    11 pages


    Remarks:

    Supp plates


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :