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The ‘Minituft’ surface flow visualisation method; experience of use in the RAE 5m pressurised low-speed wind tunnel

Published online by Cambridge University Press:  04 July 2016

D. G. Dobney ,
P. Hanson  and
S. P. Fiddes
D. G. Dobney
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough, Hants
P. Hanson
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough, Hants
S. P. Fiddes
Affiliation:
Aerodynamics Department, Royal Aircraft Establishment, Farnborough, Hants
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Summary

The development and use of a ‘minituft’ surface flow visualisation technique in the RAE 5m Pressurised Low-Speed Wind Tunnel is described.

The method, due to Crowder, uses very fine nylon monofilaments to show surface flow direction. These tufts are made visible by coating them in a fluorescent dye and then illuminating them with a powerful ultra-violet light source.

Because of their small size, a large number of tufts may be used without interfering with the flow to a great extent. However, it is shown that if accurate force measurements are required, then it is advisable to test the model in the absence of tufts.

Type
Research Article
Information
The Aeronautical Journal , Volume 90 , Issue 891 , January 1986 , pp. 10 - 17
Copyright
Copyright © Royal Aeronautical Society 1986 

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References

1. Crowder, J. P. Fluorescent minitufts for non-intrusive flow visualisation. McDonnell-Douglas Report MDC J7374, 1977.Google Scholar
2. Crowder, J. P. Add fluorescent minitufts to the aerodynami- cist's bag of tricks. Aeronautics and Astronautics, AIAA, November 1980.Google Scholar
3. Mann, M. J., Huffman, J. K., Fox, C H. JR. and CAMPBELL, R. K. Experimental study of wing leading-edge devices for improved manoeuvre performance of a supercritical manoeuvring fighter configuration. NASA TP 2125, 1983.Google Scholar
4. Arnal, D. Description and prediction of transition in two-dimensional flow. AGARD R 709, 1984.Google Scholar