Nonlinear parabolized stability equations and secondary instability analyses are used to provide a computational assessment of the potential use of the discrete roughness elements (DRE) 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 34.6deg, free-stream Mach number of 0.75 and chord Reynolds numbers of 17 x 10(exp 6), 24 x 10(exp 6) and 30 x 10(exp 6) suggest that DRE 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., DRE) also suppresses the growth of most amplified traveling crossflow disturbances.


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    Titel :

    DRE-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers


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

    Kongress:

    51st AIAA Aerospace Sciences Meeting


    Erscheinungsdatum :

    2013-01-07


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    DRE-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers

    Malik, M. / Liao, W. / Li, F. et al. | British Library Conference Proceedings | 2013


    DRE-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers

    Malik, Mujeeb / Liao, Wei / Li, Fei et al. | AIAA | 2013