A flight experiment, conducted at NASA Dryden Flight Research Center, investigated the effects of surface excrescences, specifically gaps and steps, on boundary-layer transition in the vicinity of a leading edge at transonic flight conditions. A natural laminar flow leading-edge model was designed for this experiment with a spanwise slot manufactured into the leading-edge model to simulate gaps and steps like those present at skin joints of small transonic aircraft wings. The leading-edge model was flown with the flight test fixture, a low-aspect ratio fin mounted beneath an F-104G aircraft. Test points were obtained over a unit Reynolds number range of 1.5 to 2.5 million/ft and a Mach number range of 0.5 to 0.8. Results for a smooth surface showed that laminar flow extended to approximately 12 in. behind the leading edge at Mach number 0.7 over a unit Reynolds number range of 1.5 to 2.0 million/ft. The maximum size of the gap-and-step configuration over which laminar flow was maintained consisted of two 0.06-in. gaps with a 0.02-in. step at a unit Reynolds number of 1.5 million/ft.


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    Titel :

    Transonic Flight Test of a Laminar Flow Leading Edge with Surface Excrescences


    Beteiligte:
    F. A. Zuniga (Autor:in) / A. Drake (Autor:in) / R. A. Kennelly (Autor:in) / D. J. Koga (Autor:in) / R. V. Westphal (Autor:in)

    Erscheinungsdatum :

    1994


    Format / Umfang :

    14 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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    FISCHER, M. / WRIGHT, JR., A. / WAGNER, R. | AIAA | 1983