Pressure distribution tests in full-scale wind tunnel on 2:1 tapered U S A 45 airfoil equipped with 20% chord split trailing edge flaps of various spans, indicating that only relatively small increase in normal force coefficients is to be expected by extending flap span of airfoil-flap combination beyond 70% of wing span.


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    Title :

    Full-scale span load distribution on tapered wing with split flaps of various spans


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Notes


    Contributors:


    Publication date :

    1937


    Size :

    10 pages


    Remarks:

    Bibliography, 18 Supp sheets


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :