Numerical and experimental results are presented for a new two-element, fixed-geometry natural laminar flow airfoil optimized for cruise Reynolds numbers on the order of three million. The airfoil design consists of a primary element and an independent secondary element with a primary to secondary chord ratio of three to one. The airfoil was designed to improve the cruise lift-to-drag ratio while maintaining an appropriate landing capability when compared to conventional airfoils. The airfoil was numerically developed utilizing the NASA Langley Multi-Component Airfoil Analysis computer code running on a personal computer. Numerical results show a nearly 11.75 percent decrease in overall wing drag with no increase in stall speed at sailplane cruise conditions when compared to a wing based on an efficient single element airfoil. Section surface pressure, wake survey, transition location, and flow visualization results were obtained in the Texas A&M University Low Speed Wind Tunnel. Comparisons between the numerical and experimental data, the effects of the relative position and angle of the two elements, and Reynolds number variations from 8 x 10(exp 5) to 3 x 10(exp 6) for the optimum geometry case are presented.


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    Titel :

    Two Element Laminar Flow Airfoil Optimized for Cruise


    Beteiligte:
    G. G. Steen (Autor:in)

    Erscheinungsdatum :

    1994


    Format / Umfang :

    175 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    A Two Element Laminar Flow Airfoil Optimized for Cruise

    Steen, Gregory G. | Online Contents | 1996





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