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 17×106, 24×106, and 30×106 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. Presented as Paper 2013-0412 at the 51st AIAA Aerospace Sciences Meeting, Grapewine, TX, 7-10 January 2013
Discrete-Roughness-Element-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers
AIAA journal ; 53 , 8
2015
Aufsatz (Zeitschrift)
Englisch
DRE-Enhanced Swept-Wing Natural Laminar Flow at High Reynolds Numbers
British Library Conference Proceedings | 2013
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