|Rayleigh scattering image of a turbulent boundary layer at Mach 2.5, by M.W. Smith . Flow is from left to right. Reynolds number based on momentum thickness is about 25,000 (M.W. Smith and A.J. Smits, Experiments in Fluids, 18, 288-302, 1995).|
|Filtered Rayleigh scattering image of a turbulent boundary layer at Mach 8.0, by M. Etz . Flow is from left to right. Reynolds number based on momentum thickness is about 3,600. Click to download Structure of a Mach 8 Turbulent Boundary Layer , by M.L. Baumgartner, P.J. Erbland, M.R. Etz, A. Yalin, B.K. Muzas, A.J. Smits, W.R. Lempert and R.B. Miles, AIAA Paper 97-0765, (Acrobat PDF format, 875k).|
|Laser-induced fluorescence image of an incompressible turbulent boundary layer, by C. Delo . Flow is from left to right, the flow was visualized with disodium fluorescein dye in water. Reynolds number based on momentum thickness is 700.|
The facility, data acquisition and analysis procedures, are given in:
Randall W. Smith , "Effect of Reynolds Number on the Structure of Turbulent Boundary Layers," Ph.D. Thesis, Department of Mechanical and Aerospace Engineering, Princeton University, January 1994.
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A brief description of the recommended Pitot probe velocity gradient corrections are contained in the file probecor.pdf , which can be read using Acrobat Reader.
NOTE: Further studies at Princeton have revealed that the error in measured
static pressure has a more significant effect on the mean velocity
analysis than previously recognized. A new study of this error is given
in B.J. McKeon and A.J. Smits 'Static pressure
correction in high Reynolds number fully developed turbulent pipe flow
' (2002) Meas. Sci. Tech. 13, 1608-1614.
A.J. Smits and J.P. Dussauge, "Turbulent shear layers in supersonic flows," Springer, ISBN 1-56396-260-8 ($80). To order, call 1-800-SPRINGER (or Springer Physics ), or try the Internet Book Shop .
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