Hostname: page-component-cd9895bd7-hc48f Total loading time: 0 Render date: 2024-12-22T11:16:08.751Z Has data issue: false hasContentIssue false

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

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