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Experimental results for the transpired turbulent boundary layer in an adverse pressure gradient

Published online by Cambridge University Press:  29 March 2006

P. S. Andersen
Affiliation:
Danish Atomic Energy Commission, Research Establishment Risø, Roskilde
W. M. Kays
Affiliation:
Department of Mechanical Engineering, Stanford University, Stanford, California 94305
R. J. Moffat
Affiliation:
Department of Mechanical Engineering, Stanford University, Stanford, California 94305

Abstract

An experimental investigation of the fluid mechanics of the transpired turbulent boundary layer in zero and adverse pressure gradients was carried out on the Stanford Heat and Mass Transfer Apparatus. Profiles of (a) the mean velocity, (b) the intensities of the three components of the turbulent velocity fluctuations and (c) the Reynolds stress were obtained by hot-wire anemometry. The wall shear stress was measured by using an integrated form of the boundary-layer equation to ‘extrapolate’ the measured shear-stress profiles to the wall.

The two experimental adverse pressure gradients corresponded to free-stream velocity distributions of the type uxm, where m = −0·15 and −0·20, x being the streamwise co-ordinate. Equilibrium boundary layers (i.e. flows with velocity defect profile similarity) were obtained when the transpiration velocity v0 was varied such that the blowing parameter B = pv0u0 and the Clauser pressure-gradient parameter $\beta\equiv\delta_1\tau_0^{-1}\,dp/dx $ were held constant. (τ0 is the shear stress at the wall and δ1 is the displacement thickness.)

Tabular and graphical results are presented.

Type
Research Article
Copyright
© 1975 Cambridge University Press

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References

Andersen, P. S., Kays, W. M. & Moffat, R. J. 1972 Thermosci. Div., Stanford University Rep. HMT-15.
Bradshaw, P. 1967 J. Fluid Mech. 29, 625.
Clauser, F. H. 1954 J. Aero. Sci. 21, 91.
Coles, D. E. 1962 Rand Corp. Rep. R-403-PR.
Julien, H. L., Kays, W. M. & Moffat, R. J. 1971 A.S.M.E. J. Heat Transfer, 93, 373379.
Kays, W. M. 1972 Int. J. Heat Mass Transfer, 15, 10231044.
Loyd, R. J., Moffat, R. J. & Kays, W. M. 1970 Thermosci. Div., Stanford University Rep. HMT-13.
Mclean, J. D. & Mellor, G. L. 1972 Int. J. Heat Mass Transfer, 15, 23532369.
Moffat, R. J. & Kays, W. M. 1968 Int. J. Heat Mass Transfer, 11, 15471566.
Simpson, R. N., Moffat, R. J. & Kays, W. M. 1969 Int. J. Heat Mass Transfer, 12, 771789.
Stevenson, T. N. 1963 College of Aeronautics, Cranfield Aero. Rep. no. 166.
Young, A. D. & Maas, J. N. 1936 Aero. Res. Counc. R. & M. no. 1770.