A large-chord, swept, supercritical, laminar-flow-control (LFC) airfoil was designed and constructed and is currently undergoing tests in the Langley 8 ft Transonic Pressure Tunnel. The experiment was directed toward evaluating the compatibility of LFC and supercritical airfoils, validating prediction techniques, and generating a data base for future transport airfoil design as part of NASA's ongoing research program to significantly reduce drag and increase aircraft efficiency. Unique features of the airfoil included a high design Mach number with shock free flow and boundary layer control by suction. Special requirements for the experiment included modifications to the wind tunnel to achieve the necessary flow quality and contouring of the test section walls to simulate free air flow about a swept model at transonic speeds. Design of the airfoil with a slotted suction surface, the suction system, and modifications to the tunnel to meet test requirements are discussed.


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    Titel :

    NASA (National Aeronautics and Space Administration) Langley Laminar-Flow-Control (LFC) Experiment on a Swept, Supercritical Airfoil: Design Overview


    Beteiligte:
    C. D. Harris (Autor:in) / W. D. Harvey (Autor:in) / C. W. Brooks (Autor:in)

    Erscheinungsdatum :

    1988


    Format / Umfang :

    128 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    The NASA Langley Laminar-Flow-Control (LFC) experiment on a swept, supercritical airfoil: Design overview

    Harris, Charles D. / Harvey, William D. / Brooks, Cuyler W., Jr. | NTRS | 1988


    NASA Langley laminar flow control airfoil experiment

    Harvey, W. D. / Pride, J. D. | NTRS | 1982




    The NASA Langley laminar flow control airfoil experiment

    Harvey, W. D. / Pride, J. D. | NTRS | 1982