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A note on the interpretation of mini-tuft photographs

Published online by Cambridge University Press:  04 July 2016

D. G. Mabey
Affiliation:
Department of AeronauticsImperial College of Science, Technology and Medicine London, UK
B. L. Welsh
Affiliation:
High Speed and Weapons Aerodynamics Department DRA Bedford, UK
C. R. Pyne
Affiliation:
High Speed and Weapons Aerodynamics Department DRA Bedford, UK

Abstract

Although mini-tufts are considered generally to show the surface flow direction on windswept surfaces, there is some uncertainty about their correct interpretation, particularly as three-dimensional flows approach separation. This note provides some guidance on this controversial question, based on experience with mini-tufts on wings, fins and canards in the DRA 13 ft x 9 ft low speed wind-tunnel at Bedford.

An illustration of the value of the technique is given. Mini-tuft photographs are used to identify the trailing edge condition which relates to the classification of the steady and fluctuation pressure distributions observed a swept wing with a conical, separated flow.

Type
Research Article
Copyright
Copyright © Royal Aeronautical Society 1995 

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References

1. Crowder, J.P. Fluorescent mini-tufts for non-intrusive flow visualisation, McDonnell Douglas Report MDC J7374, 1977.Google Scholar
2. Dobney, D.G., Hanson, P. and Fiddes, S.P. The “mini-tuft” surface flow visualisation method; experience of use in the RAE 5 m pressurised low-speed windtunnel, Aeronaut J, 1986, 90, (891), pp 1017.Google Scholar
3. Squire, L.C. The motion of a thin oil sheet under the steady boundary layer on a body, J Fluid Mech, 1961, 11, (2), ppl61179.Google Scholar
4. Pitman, J.L. Experimental flow field visualisation of a high alpha wing at Mach 1·62, J Aircraft, 1987, 24, (5), pp 335341.Google Scholar
5. Pitman, J.L. Private communication, 18 June 1987.Google Scholar
6. Mabey, D.G. A review of scale effects in unsteady aerodynamics. Prog Aerospace Sci, 1991, 28, (4), pp 273321.Google Scholar