Abstract
As in Chapter 6, we begin with the statement that the main difference between laminar flows and turbulent flows is that the effective diffusivities in turbulent flow are unknown. In Chapter 6 the temperature and/or concentration differences were small enough not to affect the mean velocity field, and it was assumed without explicit comment that the fluctuating velocity field, which controls the turbulent transport of momentum, heat, or mass, was also unaffected.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
Preview
Unable to display preview. Download preview PDF.
References
Rotta, J.C.:Turbulent boundary layers with heat transfer in compressible flow. AGARD Rept. 281, 1960
Van Driest, E. R.: Turbulent boundary layer in compressible fluids. J. Aeronaut. Sci. 18:145 (1951).
Fernholz, H. H. and Finley, P. J.: A critical compilation of compressible turbulent boundary-layer data. AGARDographs 223, 253, 263,1977.
Bradshaw, P.: An improved Van Driest skin-friction formula for compressible turbulent boundary layers. AIAA J., 15:212 (1977).
Fernholz, H. H.: Ein halbempirisches Gesetz für die Wandreibung in kompres- sibilen turbulenten Grenzschichten bei isothermer und adiabater Wand. Z. Angew. Math. u. Mech. 51:T146, (1971).
Mabey, D. G.: Some observations on the wake component of the velocity profiles of turbulent boundary layers at subsonic and supersonic speeds. Aero. Quart. 30:590 (1979).
Coles, D.: The turbulent boundary layer in a compressible fluid. Phys. Fluids 7:1403 (1964).
Hopkins, E. J. and Inouye, M.: An evaluation of theories for predicting turbulent skin friction and heat transfer on flat plates at supersonic and hypersonic Mach numbers. AIAA J., 9:993 (1971).
Spalding, D. B. and Chi, S. W.: The drag of a compressible turbulent boundary layer on a smooth flat plate with and without heat transfer. J. Fluid Mech. 18:117 (1964).
Hopkins, E. J. and Keener, E. R.: Pressure gradient effects on hypersonic turbulent skin-friction and boundary-layer profiles. AIAA J. 10:1141 (1972).
Cary, A. M. and Bertram, M. H.: Engineering prediction of turbulent skin friction and heat transfer in high-speed flow. NASA TN D-7507, 1974.
Cary, A. M.: Summary of available information on Reynolds analogy for zero-pressure gradient, compressible turbulent-boundary-layer flow. NASA TN D-5560, 1970.
Goddard, F. E., Jr.: Effect of uniformly distributed roughness on turbulent skin-friction drag at supersonic speeds.J. Aero/Space Sei., 26:1–15 (1959).
Fenter, F. W.: The effect of heat transfer on the turbulent skin-friction of uniformly rough surfaces in compressible flow. The University of Texas, Defense Research Lab Rept. DLR-368, CM-839, April 1956.
Moore, D. R. and Harkness, J.: Experimental investigation of the compressible turbulent boundary layer at very high Reynolds numbers, M = 2.8, Rept. No. 0.71000/4R-9, LTV Res. Center, 1964.
Matting, F. W., Chapman, D. R., Nyholm, J. R. and Thomas, A. G.: Turbulent skin friction at high Mach numbers and Reynolds numbers in air and helium. NASA TR R-82, 1961.
Cebeci, T., Smith, A. M. O. and Mosinskis, G. J.: Calculation of compressible adiabatic turbulent boundary layers. AIAA J. 8:1973 (1970).
Michel, R.: Etude de la transition sur les profiles d’aile; establissement d’un critere de determination de point de transition et calcul de la trainee de profile incompressible. ONERA Rept 1/578A, 1951.
Pappas, C. S.: Measurement of heat transfer in the turbulent boundary layer on a flat plate in supersonic flow and comparison with skin-friction results. NACA Tech. Note No. 3222, 1954.
Squire, L. C.: Further experimental investigations of compressible turbulent boundary layers with air injection. ARC R&M 3627, 1970.
Pasiuk, L., Hastings, S. M., and Chatham, R.: Experimental Reynolds analogy factor for a compressible turbulent boundary layer with a pressure gradient. Naval Ordnance Rept. NOLTR 64–200, White Oak, Maryland, 1965.
Lewis, J. E., Gran, R. L. and Kubota, T.: An experiment in the adiabatic compressible turbulent boundary layer in adverse and favorable pressure gradients. J. Fluid Mech., 51:657 (1972).
Adamson, T. C. and Messiter, A. F.: Analysis of two-dimensional interactions between shock waves and boundary layers. Ann. Rev. Fluid Mech., 12:103–138 Annual Reviews, Palo Alto, 1980.
Computation of Viscous-Inviscid Interactions. AGARD Conf. Proceedings No. 291, 1981.
Melnik, R. E.: Turbulent interactions on airfoils at transonic speeds—Recent developments. AGARD CP 291, Paper 10, 1981.
Law, C. H.: Supersonic turbulent boundary-layer separation. AIAA J. 12:1974.
Roshko, A. and Thomke, G. J.: Supersonic turbulent boundary-layer interaction with a compression corner at very high Reynolds number. Proc. Symposium on Viscous Interaction Phenomena in Supersonic Hypersonic Flow. USAF Aerospace Research Labs., Wright-Patterson AFB, Ohio, Univ. of Dayton Press, May 1969.
Hayakawa, K. and Squire, L. C.: The effect of the upstream boundary-layer state on the shock interaction at a compression corner.J. Fluid Mech. 122:369 (1982).
Lighthill, M. J.: On boundary layers and upstream influence, II, Supersonic flow without separation. Proc. Royal Soc. A, 217:1953.
Inger, G. R.: Nonasymptotic theory of unseparated turbulent boundary-layer- shock-wave interaction with application to transonic flows. In Numerical and Physical Aspects of Aerodynamic Flows (ed. T. Cebeci) p. 159, Springer-Verlag, New York 1982.
Viegas, J. R. and Horstmann, C. C.: Comparison of multiequation turbulence models for several shock boundary-layer interaction flows. AIAA J. 17:811–820, 1979
Author information
Authors and Affiliations
Rights and permissions
Copyright information
© 1988 Springer-Verlag New York Inc.
About this chapter
Cite this chapter
Cebeci, T., Bradshaw, P. (1988). Coupled Turbulent Boundary Layers. In: Physical and Computational Aspects of Convective Heat Transfer. Physical and Computational Aspects of Convective Heat Transfer. Springer, New York, NY. https://doi.org/10.1007/978-1-4612-3918-5_11
Download citation
DOI: https://doi.org/10.1007/978-1-4612-3918-5_11
Publisher Name: Springer, New York, NY
Print ISBN: 978-0-387-96821-6
Online ISBN: 978-1-4612-3918-5
eBook Packages: Springer Book Archive