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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Two Element Laminar Flow Airfoil Optimized for Cruise


    Contributors:
    G. G. Steen (author)

    Publication date :

    1994


    Size :

    175 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    A Two Element Laminar Flow Airfoil Optimized for Cruise

    Steen, Gregory G. | Online Contents | 1996





    LAMINAR FLOW WING OPTIMIZED FOR TRANSONIC AND SUPERSONIC CRUISE AIRCRAFT

    TRACY RICHARD R / CHASE JAMES D | European Patent Office | 2021

    Free access