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On the effect of wing taper and sweep direction on leading edge transition

Published online by Cambridge University Press:  04 July 2016

D. I. A. Poll  and
D. J. Paisley
D. I. A. Poll
Affiliation:
Aerodynamics Division, College of Aeronautics, Cranfield Institute of Technology, Cranfield, Bedford
D. J. Paisley
Affiliation:
Aerodynamics Division, College of Aeronautics, Cranfield Institute of Technology, Cranfield, Bedford
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Summary

An experimental study has been made of the conditions necessary to produce transition in a swept attachment-line boundary layer which is subjected to disturbances from trip wires of various sizes. The boundary layer considered is that formed on a long, untwisted, tapered wing which has been tested in both the backward swept and forward swept configurations. Results from these tests are compared with previous work on an untapered model. Some important similarities and some puzzling differences have been found. Finally consideration is given to the practical implications of this work. It is suggested that a forward swept wing may be capable of supporting a laminar attachment-line flow at a much higher free-stream Reynolds number than a corresponding swept-back wing.

Type
Research Article
Information
The Aeronautical Journal , Volume 89 , Issue 883 , March 1985 , pp. 109 - 117
Copyright
Copyright © Royal Aeronautical Society 1985 

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Footnotes

*

Present address Surveillance Systems Department, Canadair Ltd, St Laurent,Montreal, Canada

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