| タイトル | Discrete-Roughness-Element-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers |
| 本文（外部サイト） | http://hdl.handle.net/2060/20150014523 |
| 著者（英） | Liao, Wei; Choudhari, Meelan; Li, Fei; Malik, Mujeeb |
| 発行日 | 2015-03-12 |
| 言語 | eng |
| 内容記述 | 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. |
| NASA分類 | Fluid Mechanics and Thermodynamics |
| レポートNO | NF1676L-18869 |
| 権利 | Copyright, Distribution as joint owner in the copyright |
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