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The expansion of a hypersonic turbulent boundary layer at a sharp corner

Published online by Cambridge University Press:  29 March 2006

A. W. Bloy
A. W. Bloy
Affiliation:
Department of the Mechanics of Fluids, University of Manchester, England
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Abstract

A sharp wedge expansion flap was tested in the von Kámán Institute Long-shot tunnel at Mach 16 and data on the wall pressure and heat transfer were obtained. Pitot pressure measurements in the boundary layer just ahead of the expansion flap were also made. The surface data are compared with predictions from a characteristics solution for the boundary-layer expansion and from a simple heat-transfer theory.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 67 , Issue 4 , 25 February 1975 , pp. 647 - 655
Copyright
© 1975 Cambridge University Press

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References

Bushnell, D. M., Johnson, C. B., Harvey, W. D. & Feller, W. V. 1969 Comparison of prediction methods and studies of relaxation in hypersonic turbulent nozzle-wall boundary layers. N.A.S.A. Tech. Note, D-5433.Google Scholar
Coleman, G. T. & Stollery, J. L. 1972 Heat transfer from hypersonic turbulent flow at a wedge compression corner. J. Fluid Mech., 56, 741–752.Google Scholar
Delery, J. & Masure, B. 1968 Action d'une variation brusque depression sur line couche limite turbulente en écoulement supersonique. Recueil de notes sur l'Activite de l'ONERA, pp. 25–26.Google Scholar
Eckert, E. R. G. 1955 Engineering relations for skin friction and heat transfer to surfaces in high velocity flow, J. Aero. Sci. 22, 585.Google Scholar
Hopkins, E. J., Keener, E. R., Polek, T. E. & Dwyer, H. A. 1972 Hypersonic turbulent skin friction and boundary-layer profiles on non-adiabatic flat plates, A.I.A.A. J. 10 40–48.Google Scholar
Lees, L. 1956 Laminar heat transfer over blunt-nosed bodies at hypersonic flight speeds. Jet Propulsion, 26, 259–269.Google Scholar
Oosthuizen, P. H. 1967 An analysis of the interaction of a boundary layer and the corner expansion wave in supersonic flow. U.T.I.A.S. Tech. Note, no. 117.Google Scholar
Reeves, B. L. 1973 A two-layer model of high speed two- and three-dimensional turbulent boundary layers with pressure gradient, surface mass injection and entropy layer swallowing. A.I.A.A. Paper, no. 73–135.Google Scholar
Richards, B. E. & Enkenhus, K. R. 1970 Hypersonic testing in the VKI Longshot freepiston tunnel. A.I.A.A.J., 8, 1020–1025.Google Scholar
Thomann, H. 1968 Effect of streamwise wall curvature on heat transfer in a turbulent boundary layer. J. Fluid Mech., 33, 283–292.Google Scholar
Walker, G. K. 1960 A particular solution to the turbulent boundary layer equations. J. Aero. Sci., 27, 715–716.Google Scholar
Zakkay, V., Toba, K. & Kuo, T. J. 1964 Laminar, transitional and turbulent heat transfer after a sharp corner, A.I.A.A. J. 2, 1389–1395.Google Scholar