Results of wind-tunnel tests on airfoil designed according to methods published in October 25, 1927, issue of magazine, part of which is reprinted here; approximate formula is derived for airfoil profile drag applying to best smooth fair airfoils of modern design at full-flight scale; by manipulation of basic section, changing thickness or curvature of median line or both, infinite number of sections may be obtained which are affinal; layout data for basis section.


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    Title :

    An approximate expression for airfoil profile drag


    Additional title:

    Aviation


    Contributors:
    Clark, V.E. (author)

    Published in:

    Aviation ; 27 , n 12


    Publication date :

    1929


    Size :

    2 pages


    Remarks:

    3 Figs.


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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