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Discrete-Roughness-Element-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds NumbersNonlinear 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.
Document ID
20150014523
Acquisition Source
Langley Research Center
Document Type
Reprint (Version printed in journal)
External Source(s)
doi:10.2514/1.J053637
Authors
Malik, Mujeeb (NASA Langley Research Center Hampton, VA, United States)
Liao, Wei (National Inst. of Aerospace Hampton, VA, United States)
Li, Fei (NASA Langley Research Center Hampton, VA, United States)
Choudhari, Meelan (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
July 30, 2015
Publication Date
March 12, 2015
Publication Information
Publication: AIAA Journal
Volume: 53
Issue: 8
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
NF1676L-18869
Funding Number(s)
WBS: WBS 794072.02.07.02.01
Distribution Limits
Public
Copyright
Public Use Permitted.

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