Hostname: page-component-586b7cd67f-rcrh6 Total loading time: 0 Render date: 2024-11-25T05:42:54.105Z Has data issue: false hasContentIssue false
  • English
  • Français

Supersonic Turbulent Boundary Layers: Some Comparisons Between Experiment and a Simple Theory

Published online by Cambridge University Press:  07 June 2016

J L Stollery
J L Stollery*
Affiliation:
Cranfield Institute of Technology
Get access

Summary

Comparisons are made between some measurements of skin friction and heat transfer over five axisymmetric bodies and the predictions of a simple theory. The development of the theory is outlined and explicit expressions obtained for all the gross turbulent boundary-layer characteristics (δ*,θ,H,Cf and St).

Type
Research Article
Information
Aeronautical Quarterly , Volume 27 , Issue 2 , May 1976 , pp. 87 - 98
Copyright
Copyright © Royal Aeronautical Society. 1976

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 Spence, D A The growth of compressible turbulent boundary layers on isothermal and adiabatic walls. ARC R&M 3191, 1961.Google Scholar
2 Stollery, J L Bates, L Turbulent hypersonic viscous interaction. Journal of Fluid Mechanics, Vol 63, p 145, 1974.Google Scholar
3 Stollery, J L Coleman, G T A correlation between pressure and heat transfer distributions at supersonic and hypersonic speeds. Aeronautical Quarterly, Vol XXVI, p 304, 1975.Google Scholar
4 Cheng, H K Hall, J G Golian, T C Hertzberg, A Boundary-layer displacement and leading-edge bluntness effects in high-temperature hypersonic flow. Journal of the Aerospace Sciences, Vol 28, p 353, 1961.Google Scholar
5 Stollery, J L Turbulent boundary-layer growth at hypersonic speeds. Imperial College Aero Report 73-04, 1973.Google Scholar
6 Eckert, E R G Engineering relations for skin friction and heat transfer to surfaces in high velocity flow. Journal of the Aeronautical Sciences, Vol 22, p 585, 1955.Google Scholar
7 Lewis, J E Gran, R L Kubota, T An experiment on the adiabatic compressible turbulent boundary layer in adverse and favourable pressure gradients. Journal of Fluid Mechanics, Vol 51, p 657, 1972.CrossRefGoogle Scholar
8 Gran, R L Lewis, J E Kubota, T The effect of wall cooling on a compressible turbulent boundary layer. Journal of Fluid Mechanics, Vol 66, p 507, 1974.CrossRefGoogle Scholar
9 Peake, D J Brakmann, G Romeskie, J M Comparisons between some high Reynolds number turbulent boundary-layer experiments at Mach 4, and various recent calculation procedures. AGARD Conference Proceedings 93, 1971.Google Scholar
10 Horstman, C C Kussoy, M I Coakley, T J Rubesin, M W Marvin, J G Shock-wave-induced turbulent boundary-layer separation at hypersonic speeds. AIAA Paper 75-4, 1975.Google Scholar
11 Bradshaw, P The effect of mean compression or dilatation on the turbulence structure of supersonic boundary layers. Journal of Fluid Mechanics, Vol 63, p 449, 1974.Google Scholar
12 Kussoy, M I Horstman, C C Rubesin, M W Coakley, T J Kussoy, M I An experimental documentation of a hypersonic shock-wave turbulent boundary-layer interaction flow - with and without separation. NASA TM X-62412, 1975.Google Scholar
13 Marvin, J G Horstman, C C et al An experimental and numerical investigation of shock-wave induced turbulent boundary-layer separation at hypersonic speeds. AGARD Conference Proceedings 168, 1975.Google Scholar
14 Hoydysh, W G Zakkay, V An experimental investigation of hypersonic turbulent boundary layers in an adverse pressure gradient. AIAA Journal, Vol 7, p 105, 1969.Google Scholar
15 Neal, L Bertram, M H Turbulent skin friction and heat-transfer charts adapted from the Spalding and Chi method. NASA TN D-3969, 1967.Google Scholar