Welcome to the Princeton Gas Dynamics Lab Home Page!
The Gas Dynamics Laboratory is part of the
Department of Mechanical and Aerospace Engineering
at Princeton University
. It is located on the Forrestal Campus, Princeton, NJ 08544.
Main Menu
Click on any of the hyperlinks below to obtain more information about GDL.
Vortex rings
Vortex dipoles
Find out more about eels and see the new
eel movie
PRAY (mechanical fish)
Electo Active Polymers as flow actuators
HRTF Homepage
MHz Rate Imaging on Elliptic Cones


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, 288302,
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 970765, (Acrobat PDF format,
875k). 


Laserinduced 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. 
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The mean velocity and turbulence profiles obtained in
a flat plate, incompressible boundary layer for Reynolds numbers based on
momentum thickness of about 5,000 to 13,000 are now available. Please click
on the link given below to obtain the data files. The files are text files
and can be read by Excel. There is a ReadMe file that describes the format
in detail.
Boundary Layer Data :
Macintosh
data
and
DOS data
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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The mean velocity profiles obtained in the Superpipe
facility are now available. Please click on the links given below to obtain
the data files for each Reynolds number. The files are text files. The Reynolds
number is based on pipe diameter and average velocity. There are 26 profiles
altogether. The data have not been corrected for Pitot tube displacement
effects, nor for any other effects. The facility is described
here
. For a more complete description of the facility, data acquisition and
analysis procedures, including recommendations on corrections for Pitot tube
displacement effects, see:
Mark V. Zagarola
, "Mean Flow Scaling of Turbulent Pipe Flow," Ph.D. Thesis, Department
of Mechanical and Aerospace Engineering, Princeton University, June 1996.
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, 16081614.
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Available now:
A.J. Smits and J.P. Dussauge, "Turbulent shear
layers in supersonic flows," Springer, ISBN 1563962608 ($80). To order,
call 1800SPRINGER (or
Springer Physics
), or try the Internet
Book Shop
.
Related Information and WWW Sites
The other sites
file contains references to several sites with helpful information.
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This page last updated July 27, 1998 (isa).