Scale-effect tests in turbulent tunnel of NACA 653- 418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap. (Advance Confidential Report L4122 Sept 1944)


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    Title :

    Scale-effect tests in turbulent tunnel of NACA 653- 418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap


    Additional title:

    Nat Advisory Committee Aeronautics -- Wartime Report


    Contributors:


    Publication date :

    1944


    Size :

    10 pages


    Remarks:

    9 Supp plates


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :