Nonlinear parabolized stability equations and secondary-instability analyses are used to provide a computational assessment of the potential use of the discrete-roughness-element technology for extending swept-wing natural laminar flow at chord Reynolds numbers relevant to transport aircraft. Computations performed for the boundary layer on a natural-laminar-flow airfoil with a leading-edge sweep angle of 34.6 deg, freestream Mach number of 0.75, and chord Reynolds numbers of 17 × 10(exp 6), 24 × 10(exp 6), and 30 × 10(exp 6) suggest that discrete roughness elements could delay laminar-turbulent transition by about 20% when transition is caused by stationary crossflow disturbances. Computations show that the introduction of small-wavelength stationary crossflow disturbances (i.e., discrete roughness element) also suppresses the growth of most amplified traveling crossflow disturbances.


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    Titel :

    Discrete-Roughness-Element-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers


    Beteiligte:
    Malik, Mujeeb (Autor:in) / Liao, Wei (Autor:in) / Li, Fei (Autor:in) / Choudhari, Meelan (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2015-03-12


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch






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