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Hot-Wire Measurements of the Influence of Surface Steps on Transition in Favorable Pressure Gradient Boundary Layers

Gerashchenko, S. and McKeon, B. J. and Westphal, R. V. and Bender, A. M. and Drake, A. (2010) Hot-Wire Measurements of the Influence of Surface Steps on Transition in Favorable Pressure Gradient Boundary Layers. In: 48th AIAA Aerospace Sciences Meeting, January 4-7, 2010, Orlando, FL.

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An examination of the effects of surface step excrescences on boundary layer transition was performed, using a unique experimental facility. The objective of the work was to characterize the variation of transition Reynolds numbers with measurable step size and boundary layer parameters, with the specific goal of specifying new tolerance criteria for laminar flow airfoils, alongside a fundamental investigation of boundary layer transition mechanisms. This paper focuses on interpretation of hot-wire measurements, including supporting stability calculations, undertaken as part of the study. The results for both forward and aft-facing steps indicated a substantial stabilizing effect of favorable pressure gradient on excrescence-induced boundary layer transition. These findings suggest that manufacturing tolerances for laminar flow aircraft could be loosened in areas where even mild favorable pressure gradients exist.

Item Type:Conference or Workshop Item (Paper)
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McKeon, B. J.0000-0003-4220-1583
Additional Information:© 2010 Northrop Grumman. The authors acknowledge funding and support from the Air Force Research Laboratory, Prof. Mike Gaster of Queen Mary College, University of London, for the use of the Rapid-N code, and Prof. Bill Saric for useful advice.
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Air Force Research LaboratoryUNSPECIFIED
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AIAA Paper2010-374
Record Number:CaltechAUTHORS:20150303-111551041
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:55466
Deposited By: Jamie Sei
Deposited On:03 Mar 2015 22:53
Last Modified:10 Nov 2021 20:46

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