The Langley Research Center has designed a swept, supercritical airfoil incorporating Laminar Flow Control for testing at transonic speeds. Analytical expressions have been developed and an evaluation made of the experimental section drag, composed of suction drag and wake drag, using theoretical design information and experimental data. The analysis shows that, although the sweep-induced boundary-layer crossflow influence on the wake drag is too large to be ignored and there is not a practical method for evaluating these crossflow effects on the experimental wake data, the conventional unswept 2 dimensional wake-drag computation used in the reduction of the experimental data is at worst 10 percent too high.


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    Title :

    NASA (National Aeronautics and Space Administration) Langley Laminar-Flow-Control Experiment on a Swept, Supercritical Airfoil - Drag Equations


    Contributors:
    C. W. Brooks (author) / C. D. Harris (author) / W. D. Harvey (author)

    Publication date :

    1989


    Size :

    42 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English