Information is given on changes in forces on each wing of biplane cellule for various combinations of stagger and gap, stagger and sweep-back, stagger and decalage, and gap and decalage; since each test was carried up to 90 deg. angle of attack, results may be used in study of stalled flight and of spinning as well as in structural design of biplane wings.


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    Title :

    Wind tunnel pressure distribution tests on series of biplane wing models


    Additional title:

    Nat. Advisory Committee Aeronautics -- Tech. Notes


    Contributors:
    Knight, M. (author) / Noyes, R.W. (author)


    Publication date :

    1929


    Size :

    6 pages


    Remarks:

    36 Figs. on Supp plates


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :