Hostname: page-component-cd9895bd7-p9bg8 Total loading time: 0 Render date: 2024-12-24T18:02:18.995Z Has data issue: false hasContentIssue false
  • English
  • Français

Transition in the Infinite Swept Attachment Line Boundary Layer

Published online by Cambridge University Press:  07 June 2016

D.I.A. Poll
D.I.A. Poll*
Affiliation:
College of Aeronautics, Cranfield Institute of Technology
Get access

Summary

The transition behaviour of the boundary layer which is formed along an infinite swept attachment line has been studied experimentally. Circular trip wires and turbulent flat plate boundary layers have been used as sources of disturbance and the range of parameters covered has been such that the results are directly applicable to full scale flight conditions. Simple criteria have been deduced which allow the state of the boundary layer to be determined for given geometric and free stream properties. Sample calculations for typical swept wing configurations suggest that the majority of civil aircraft will have turbulent attachment lines in the cruise and that subsequent relaminarisation in regions of favourable pressure gradient is unlikely.

Type
Research Article
Information
Aeronautical Quarterly , Volume 30 , Issue 4 , November 1979 , pp. 607 - 629
Copyright
Copyright © Royal Aeronautical Society. 1979

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 Gray, W.E. The effect of wing sweep on laminar flow. RAE TM 255, (ARC 14,929), 1952 Google Scholar
2 Gray, W.E. The nature of the boundary layer flow at the nose of a swept wing. RAE TM 256 (ARC 15,021), 1952 Google Scholar
3 Owen, P.R. and Randall, D.G. Boundary layer transition on a sweptback wing. RAE TM 277 (ARC 15,022), 1952 Google Scholar
4 Gregory, N., Stuart, J.T. and Walker, W.S. On the stability of three dimensional boundary layers with application to the flow due to a rotating disc. Philosophical Transactions of the Royal Society of London, Series A, Vol. 248 pp 155–199, 1955 Google Scholar
5 Pfenninger, W. Laminar flow control - Laminarization. Special course on concepts for drag reduction, AGARD Report 654, March 1977 Google Scholar
6 Gregory, N. and Love, E.M. Laminar flow on a swept leading edge - final progress report. NPL Aero. Memo. 26, 1965 Google Scholar
7 Gaster, M. On the flow along swept leading edges. The Aeronautical Quarterly Vol. XVIII, pp 165–184, May 1967 CrossRefGoogle Scholar
8 Cumpsty, N.A. and Head, M.R. The calculation of the three-dimensional turbulent and boundary layer. Part III Comparison of attachment line calculations with experiment. The Aeronautical Quarterly, Vol. XX, pp 99–113, May 1969 CrossRefGoogle Scholar
9 Kayalar, L. Experimentelle und theoretische untersuchungen über den einfluss des turbulenzgrads auf der wärmeübergang in der umgebung des straupunkts eines kreiszylinders. Forschung im Ingenieurwesen, Vol. 35, pp 157–167, 1969 Google Scholar
10 Cumpsty, N.A. and Head, M.R. The calculation of three-dimensional turbulent boundary layers. Part II attachment line flow on an infinite swept wing. The Aeronautical Quarterly, Vol. XVIII, pp 150–164, May 1967 CrossRefGoogle Scholar
11 Beckwith, I.E. Similar solutions for the compressible boundary layer on a yawed cylinder with transpiration cooling. NASA Technical Report R-42, 1959 Google Scholar
12 Rosenhead, L. (ed.) Laminar Boundary Layers. Oxford University Press, 1963 Google Scholar
13 Poll, D.I.A. Some aspects of the flow near a swept attachment line with particular reference to boundary layer transition. College of Aeronautics Report 7805, August 1978 Google Scholar
14 Jaffe, N.A., Okamura, T.T. and Smith, A.M.O. Determination of spatial amplification factors and their application to predicting transition. AIAA Journal, Vol. 8, No. 2, pp 301–308, February 1970 CrossRefGoogle Scholar
15 Carlson, J.C. Investigation of the laminar flow characteristics of a 33 swept suction wing at high Reynolds numbers in the NASA Ames 12′ pressure wind tunnel. Northrop Report N0R-66-58, January 1966 Google Scholar
16 Gibbings, J.C. On boundary layer transition wires. ARC Cp 462, December 1958 Google Scholar
17 Narasimha, R. and Sreenivasan, K.R. Relaminarisation in highly accelerated turbulent boundary layers. Journal of Fluid Mechanics, Vol. 61, No. 3, pp 417–447, 1973 CrossRefGoogle Scholar