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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    Title :

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


    Contributors:
    F. A. Zuniga (author) / A. Drake (author) / R. A. Kennelly (author) / D. J. Koga (author) / R. V. Westphal (author)

    Publication date :

    1994


    Size :

    14 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Transonic flight test of a laminar flow leading edge with surface excrescences

    Zuniga, Fanny A. / Drake, Aaron / Kennelly, Robert A., Jr. et al. | NTRS | 1994



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    M. C. Fischer / A. S. Wright / R. D. Wagner | NTIS | 1983


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    Fischer, M. C. / Wright, A. S., Jr. / Wagner, R. D. | NTRS | 1983


    A flight test of laminar flow control leading-edge systems

    Fischer, M. C. / Wright, A. S., Jr. / Wagner, R. D. | NTRS | 1983