Hostname: page-component-5c6d5d7d68-wpx84 Total loading time: 0 Render date: 2024-08-14T22:13:43.964Z Has data issue: false hasContentIssue false
  • English
  • Français

Direct and inverse integral calculation methods for three-dimensional turbulent boundary layers

Published online by Cambridge University Press:  04 July 2016

P. D. Smith
P. D. Smith*
Affiliation:
Royal Aircraft Establishment, Bedford
Get access Rights & Permissions [Opens in a new window]

Extract

It is both a privilege and a pleasure to be asked to contribute to an edition of the Aeronautical Journal to celebrate Professor Alec Young's 70th birthday. He has been my mentor for nearly a quarter of a century.

The subject of integral prediction methods for boundary layers is one with which Alec Young has long been associated. Starting with a method for laminar compressible flow he has guided the development of, amongst others, integral methods for compressible laminar flow with heat transfer, three-dimensional laminar flow, three-dimensional turbulent flow and flows with pressure gradients normal to the surface.

This paper attempts to describe the integral methods for compressible turbulent boundary layers which are most widely used in aerodynamic design and to discuss the application of inverse integral methods to three-dimensional separated flows.

Type
Research Article
Information
The Aeronautical Journal , Volume 88 , Issue 875 , May 1984 , pp. 155 - 159
Copyright
Copyright © Royal Aeronautical Society 1984 

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. Young, A. D. Skin friction in the laminar boundary layer in compressible flow. Aero Quarterly, 1949, 1, 137–164.Google Scholar
2. Luxton, R. E. and Young, A. D. Generalised methods for the calculationofthelaminarcompressibleboundary layer characteristics with heat transfer and non-uniform pressure distribution. ARC R&M 3233, 1960.Google Scholar
3. Smith, P. D. and Young, A. D. Approximate solutions of the three-dimensional laminar boundary layer momentum integral equations. ARC CP1064, 1967.Google Scholar
4. Smith, P. D. Calculation methods for three-dimensional turbulent boundary layers. ARC R&M 3523, 1966.Google Scholar
5. Myring, D. F. The effects of normal pressure gradients on the boundary layer momentum integral equation. RAE TR 68214, 1968.Google Scholar
6. Smith, P. D. The numercial computation of three-dimensional boundary layers. Three-dimensional turbulent boundary layers. IUTAMSymposiumBerlin, 29thMarch/lst April 1982, Springer-Verlag, 1982.Google Scholar
7. Smith, P. D. A calculation method for the turbulent boundary layer on an infinite yawed wing in compressible, adiabatic flow. ARC CP 1268, 1972.Google Scholar
8. Ashill, P. R. and Smith, P. D. An integral method for calculating the effects on turbulent boundary layer development of sweep and taper. RAE TR 83053, 1983.Google Scholar
9. Lock, R. C. and Firmin, M. C. P. Survey of techniques for estimating viscous effects in external aerodynamics. Numerical methods in aeronautical fluid dynamics, Roe, P. Ed. Academic Press, 1982.Google Scholar
10. Smith, P. D. An integral prediction method for three- dimensional compressible turbulent boundary layers. ARC R&M 3739, 1972.Google Scholar
11. Mager, A. Generalisation of boundary layer momentum integral equations to three-dimensional flows including those of rotating sytems. NACA Report 1067, 1952 Google Scholar
12. Smith, P. D. Calculations with the three-dimensional lagentrainment method. Proc. SSPA-ITTC Workshop on ship boundary layers 1980. Publications of SSPA Nr 90, 1981.Google Scholar
13. Green, J. E., Weeks, D. J. and Brooman, J. W. F. Prediction of turbulent boundary layers and wakes in compressible flow by a lag entrainment method. ARC R&M 3791,1973.Google Scholar
14. Stock, H. W. Calculation of three-dimensional boundary layers on wings and bodies of revolution. Proceedings DEA meeting ‘Viscous and interacting flowfield effects’. Meersburg, April 1979.Google Scholar
15. Cross, A. G. T. Calculation of compressible three-dimensional turbulent boundary layers with particular reference to wings and bodies. British Aerospace Brough YAD 3379, 1979.Google Scholar
16. Cousteix, J. Analyse theorique et moyens de prevision de la couche limite turbulente tridimensionelle. ONERA Pub. 157, 1974. English translation ESA TT-238, 1976.Google Scholar
17. Cousteix, J. Progres dans les methodes de calcul des couche limites turbulentes bi et tridimensionelles. 13eme Colloque d'Aerodynamique Appliquèe, Lyon, 8th-10th November 1976.Google Scholar
18. Myring, D. F. An integral prediction method for three- dimensional turbulent boundary layers in incompressible flow. RAE Technical Report 70147, 1970.Google Scholar
19. Wigton, L. and Yoshihara, H. Viscous-inviscid interactions with a three-dimensional inverse boundary layer code. Second symposium on numerical and physical aspects of aerodynamic flows. Long Beach California, 17th-20th January 1983.Google Scholar
20. East, L. F. Computation of three-dimensional turbulent boundary layers. EUROMECH 60 Trondheim 1975. FFA TN AE-1211, 1975.Google Scholar
21. Humphreys, D. A. Comparison of boundary layer calculations for a wing: the May 1978 Stockholm Workshop test case. FFA TN. AE-1522, 1979.Google Scholar
22. Lindhout, J. P. F., Van Den Berg, B. and Elsenaar, A. Comparison of boundary layer calculations for the root section of a wing. The September 1979 Amsterdam Workshop test case. NLR MP80028U, 1980.Google Scholar
23. Cousteix, J. Turbulent modelling and boundary layer cal culation methods. ONERA Rapport Technique OA 43/2259 AYD (DERAT 27/5004 DY), 1981.Google Scholar
24. Van Den Berg, B. and Elsenaar, A. Measurements in a three-dimensional incompressible turbulent boundary layerinan adverse pressure gradient under infinite swept wing conditions. NLR TR 720920, 1972.Google Scholar
25. Cebeci, T., Kaups, K. and Ramsey, J. A. A general method for calculating three-dimensional compressible laminar and turbulent boundary layers on arbitrary wings. NASA CR 2777, 1977.Google Scholar
26. Yoshihara, H. Private Communication.Google Scholar