Formula derived for pressure distribution under assumption of ratio of span to average chord (aspect ratio) that is not too small; range of validity of formula, so far as aspect ratio limitations are concerned, is not less than range of validity of lifting line theory for non-oscillating wing.


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    Title :

    Effect of finite span on airload distributions for oscillating wings -- I: aerodynamic theory of oscillating wings of finite span


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1947


    Size :

    39 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :