Hostname: page-component-78c5997874-v9fdk Total loading time: 0 Render date: 2024-11-05T11:24:26.473Z Has data issue: false hasContentIssue false
  • English
  • Français

Re-Developing Turbulent Boundary Layers Behind Yawed Separation Bubbles

Published online by Cambridge University Press:  07 June 2016

H P Horton
H P Horton*
Affiliation:
Queen Mary College, University of London
Get access

Summary

Measurements are presented of the mean flow properties of some three-dimensional turbulent boundary layers re-developing after reattachment behind short separation bubbles yawed at 26.5° to the main stream. For these measurements, Rθ11 varied from about 550 to 1450. It was found that, where the pressure gradient parameter (ν/ρu3τ1)∂p/∂s was not greater than about 0.05, the flow in the local external streamline direction conformed well with empirical laws for fully-attached two-dimensional layers with regard to the mean velocity profiles, shape parameter relationships and skin friction laws, giving support to the usual assumption that these two-dimensional relationships may be applied to the streamwise flow in three-dimensional layers, subject to the limitation on the pressure gradient parameter. The cross-flow profiles, on the other hand, were not generally fitted well by the often-used representations of Mager and Johnston. The variations of the kinetic energy dissipation coefficient and the entrainment rate were deduced for one of the layers, both quantities being found to be higher than those predicted by empirical relationships for conventionally-developing two-dimensional layers. However, the energy dissipation is in fair agreement with that in a similarly re-developing two-dimensional flow.

Type
Research Article
Information
Aeronautical Quarterly , Volume 23 , Issue 3 , August 1972 , pp. 211 - 228
Copyright
Copyright © Royal Aeronautical Society. 1972

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. Horton, H P Laminar separation bubbles in two- and three-dimensional incompressible flow. PhD Thesis, Queen Mary College, University of London, 1968.Google Scholar
2. Mueller, T J Korst, H H Chow, W L On the separation, re-attachment and re-development of incompressible turbulent shear flow. Journal of Basic Engineering, Series D in Transactions of the American Society of Mechanical Engineers, Vol 86, 2, p 221, June 1964.Google Scholar
3. Bradshaw, P Ferriss, D H The response of a retarded equilibrium turbulent boundary layer to the sudden removal of pressure gradient. National Physical Laboratory, Aero Report 1145, 1965.Google Scholar
4. Wallis, R A Boundary layer transition at the leading edge of thin wings and its effect on general nose separation, p 161 of Advances in Aeronautical Sciences, Vol 3, Pergamon Press, 1962.CrossRefGoogle Scholar
5. Thwaites, B The production of lift independently of incidence. ARC R & M 2611, 1947.Google Scholar
6. Woodward, D S An investigation of the flow in separation bubbles. PhD Thesis, Queen Mary College, University of London, 1970.Google Scholar
7. Tani, I Experimental investigation of flow over a step, p 377 of Proceedings of Boundary Layer Research Symposium, Freiburg, 1957 (Editor Görtler, H), Springer, 1958.Google Scholar
8. Thompson, B G J A new two-parameter family of mean velocity profiles for incompressible turbulent boundary layers on smooth walls. ARC R & M 3463, 1965.Google Scholar
9. Johnston, J P On the three-dimensional turbulent boundary layer generated by a secondary flow. Journal of Basic Engineering, Series D in Transactions of the American Society of Mechanical Engineers, Vol 82, p 233, March 1960.Google Scholar
10. Coles, D The law of the wake in the turbulent boundary layer. Journal of Fluid Mechanics, Vol 1, p 191, 1956.Google Scholar
11. Bradbury, L J S The structure of a self-preserving plane jet. Journal of Fluid Mechanics, Vol 23, p 31, 1965.Google Scholar
12. Hall, M G Experimental measurements in a three-dimensional turbulent boundary layer in supersonic now. AGARDograph 97, p 829, 1965.Google Scholar
13. Smith, P D An investigation into three-dimensional boundary layers. PhD Thesis, Queen Mary College, University of London, 1965; see also ARC R & M 3523, 1966.Google Scholar
14. Clauser, F H The turbulent boundary layer, p 1 of Advances in Applied Mechanics, Vol 4, Academic Press, 1956.Google Scholar
15. van Driest, E R On turbulent flow near a wall. Journal of the Aeronautical Sciences, Vol 23, p 1007, November 1956.Google Scholar
16. Ludwieg, H Tillmann, W Investigation of the wall shearing stress of turbulent boundary layers. NACA TM 1285, 1950.Google Scholar
17. Perry, A E Bell, J B Joubert, P N Velocity and temperature profiles in adverse pressure gradient turbulent boundary layers. Journal of Fluid Mechanics, Vol 25, p 299, 1966.Google Scholar
18. McDonald, H The supersonic base pressure problem: a comparison between a theory and some experimental evidence. Aeronautical Quarterly, Vol XVII, p 105, May 1966.Google Scholar
19. Cumpsty, N A Head, M R The calculation of three-dimensional turbulent boundary layers. Part IV: Comparison of measurements with calculations on the rear of a swept wing. Aeronautical Quarterly, Vol XXI, p 121, May 1970.CrossRefGoogle Scholar
20. Head, M R Entrainment in the turbulent boundary layer. ARC R & M 3152, 1958.Google Scholar
21. Mager, A Generalisation of boundary layer momentum integral equations to three-dimensional flows, including those of a rotating system. NACA Report 1067, 1952.Google Scholar
22. Perry, A E Joubert, P N A three-dimensional turbulent boundary layer. Journal of Fluid Mechanics, Vol 22, p 285, 1965.CrossRefGoogle Scholar
23. Cooke, J C Boundary layers in three dimensions. AGARD Report 273, 1960; also p 221 in Progress in Aeronautical Sciences, Vol 2, Pergamon Press, 1962.Google Scholar
24. Cumpsty, N A Head, M R The calculation of three-dimensional turbulent boundary layers. Part I: Flow over the rear of an infinite swept wing. Aeronautical Quarterly, Vol XVIII, p 55, February 1967.Google Scholar
25. Cooke, J C An axially symmetric analogue for general three-dimensional boundary layers. ARC R & M 3200, 1959.Google Scholar