This study focuses on the development of wing leading edge concepts for noise reduction during high-lift operations, without compromising landing stall speeds, stall characteristics or cruise performance. High-lift geometries, which can be obtained by conventional mechanical systems or morphing structures have been considered. A systematic aerodynamic analysis procedure was used to arrive at several promising configurations. The aerodynamic design of new wing leading edge shapes is obtained from a robust Computational Fluid Dynamics procedure. Acoustic benefits are qualitatively established through the evaluation of the computed flow fields.


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    Title :

    Wing Leading Edge Concepts for Noise Reduction


    Contributors:
    A. Shmilovich (author) / Y. Yadlin (author) / D. M. Pitera (author)

    Publication date :

    2010


    Size :

    12 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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