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On the effects of boundary-layer transition on a cylindrical afterbody at incidence in low-speed flow

Published online by Cambridge University Press:  04 July 2016

D. I. A. Poll
D. I. A. Poll*
Affiliation:
Aerodynamics Division, College of Aeronautics, Cranfield Institute of Technology
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Extract

The experimentally observed changes in the location of boundary layer separation on the cylindrical afterbody of a tangent-ogive-cylinder, placed at incidence in a uniform flow, are related to the phenomenon of laminar-turbulent transition. Existing knowledge of the transition mechanisms which operate in general, three-dimensional; boundary layers, is described and simple prediction criteria are derived for this configuration. These criteria are compared with the currently available empirical methods for the prediction of critical Reynolds numbers for such flows. It is demonstrated that the methods which have been published to date are incomplete and the accompanying analyses are based upon superficial and erroneous physical arguments. The implications of boundary layer transition on the normal forces generated by a cylindrical afterbody are also discussed. Finally, the possibility of using transition fixing to establish ‘high Reynolds number’ separated flows in ‘low Reynolds number’ wind-tunnel facilities is briefly considered.

Type
Research Article
Information
The Aeronautical Journal , Volume 89 , Issue 888 , October 1985 , pp. 315 - 327
Copyright
Copyright © Royal Aeronautical Society 1985 

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