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The Calculation of the Three-Dimensional Turbulent Boundary Layer: Part III. Comparison of Attachment-Line Calculations with Experiment

Published online by Cambridge University Press:  07 June 2016

N. A. Cumpsty  and
M. R. Head
N. A. Cumpsty
Affiliation:
Cambridge University Engineering Department
M. R. Head
Affiliation:
Cambridge University Engineering Department
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Summary

Wind tunnel measurements have been made of the attachment-line boundary layer on a swept wing. The combination of a 4-5 in (114 mm) nose radius and 60° angle of sweep enabled a wide range of values of the parameter V2/(v dU/dx) (denoted here by C*), to be covered, and gave a thick enough boundary layer for the velocity profiles to be accurately measured. Pitot traverses were performed for values of C* from 0·59 × 105 to 3·7 × 105. Without a trip wire fitted the attachment-line flow was laminar over the full range and the measured velocity profiles agreed closely with the theory for an infinite swept wing. With a large trip wire fitted, a transition régime was observed in the range 0·6 × 105 < C* < 1·4 × 105, and at higher values of C* the flow was fully turbulent and showed good agreement with the earlier calculations of Cumpsty and Head. Preston tubes were used for skin friction measurements in fully turbulent conditions and a hot wire was used to explore the development of turbulence in the transition régime.

Type
Research Article
Information
Aeronautical Quarterly , Volume 20 , Issue 2 , May 1969 , pp. 99 - 113
Copyright
Copyright © Royal Aeronautical Society. 1969

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References

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