In recent years, the National Aeronautics and Space Administration (NASA) in cooperation with U.S. industry has performed flight and wind-tunnel investigations aimed at demonstrating the feasibility of obtaining significant amounts of laminar boundary-layer flow at moderate Reynolds numbers on the swept-back wings of commercial transport aircraft. Significant local drag reductions have been recorded with the use of a hybrid laminar flow control (HLFC) concept. In this paper, we address the potential application of HLFC to the external surface of an advanced, high bypass ratio turbofan engine nacelle with a wetted area which approaches 15 percent of the wing total wetted area of future commercial transports. A pressure distribution compatible with HLFC is specified and the corresponding nacelle geometry is computed utilizing a predictor/corrector design method. Linear stability calculations are conducted to provide predictions of the extent of the laminar boundary layer. Performance studies on an advanced twin-engine transport configuration are presented to determine potential benefits in terms of reduced fuel consumption.


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    Title :

    Hybrid Laminar Flow Control Applied to Advanced Turbofan Engine Nacelles


    Additional title:

    Sae Technical Papers


    Contributors:
    Collier, F. S. (author) / Arcara, P. C. (author) / Wie, Y. S. (author)

    Conference:

    Aerospace Atlantic Conference & Exposition ; 1992



    Publication date :

    1992-04-01




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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