Low-speed wind tunnel tests were conducted of a pressure-tapped wing model tha spanned the test section and was located downstream of a half-wing model that generated a tip vortex. Tests of this perpendicular vortex-airfoil interactions showed that the vortex caused a substantial change in the pressure distribution of the downstream wing and also exhibited a spanwise drift as it passed over the wing. The spanwise drift was in the same direction as the spanwise component of the induced flow at the wing surface, and may be attributed to an image effect, similar to the drifting apart of a wing's trailing vortices as they approach ground. Keywords: Vortices; Airfoils; Wind tunnel tests; Reprints.


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    Title :

    Vortex-Airfoil Interaction Tests


    Contributors:
    D. D. Seath (author) / D. R. Wilson (author)

    Publication date :

    1986


    Size :

    6 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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