Optimum airfoils in the sense of maximum lift coefficient are obtained for incompressible fluid flow at large Reynolds number. The maximum lift coefficient is achieved by requiring that the turbulent skin friction be zero in the pressure rise region on the airfoil upper surface. Under this constraint, the pressure distribution is optimized. The optimum pressure distribution is a function of Reynolds number and the trailing edge velocity. Geometries of those airfoils which will generate these optimum pressure distributions are obtained using a direct-iterative method which is developed in this study. This method can be used to design airfoils consisting of any number of elements. Numerical examples of one- and two-element airfoils are given. The maximum lift coefficients obtained range from 2 to 2.5.


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    Title :

    Multiple element airfoils optimized for maximum lift coefficient.


    Contributors:

    Published in:

    Publication date :

    1972-12-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Multiple element airfoils optimized for maximum lift coefficient.

    ORMSBEE, A. I. / CHEN, A. W. / NASA, Langley Research Center et al. | AIAA | 1972


    Optimization of airfoils for maximum lift

    LIEBECK, R. / ORMSBEE, A. | AIAA | 1969


    Optimization of airfoils for maximum lift

    LIEBECK, R. H. | AIAA | 1970


    On the design for maximum lift airfoils

    Lyrintzis, A.S. / Farmer, J.D. | Tema Archive | 1991