SYNOPSIS Development of the velocity and temperature of the flow behind a shock wave propagating in atmospheric air in a smooth rectangular duct has been followed by hot wire anemometry. Averaged data were analyzed iteratively to yield the velocity and temperature at several points. Property distributions close to the wave front are non-uniform. Far from the front, the steady velocity profile is approximately the same as for flow in a rectangular duct. The temperature profile develops in a similar manner to the velocity but it is difficult to define the boundary layer edge because the temperature decreases with time.
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References
1.
DeckkerB.E.L.WeekesM.E., “The Unsteady Boundary Layer in a Shock Tube”, accepted for publication, Inst. of Mech. Engrs., London.
2.
WallaceF.J.NassifM., “The Effect of Friction on Compression and Rarefaction Waves of Finite Amplitude”, Engineering1953175, 674.
3.
TrimpiR.L.CohenN.B., “A Theory for Predicting the Flow of Real Gases in Shock Tubes with Experimental Verification”, NACA TN 3375, 1955.
4.
MirelsH.BraunW.H., “Non-Uniformities in Shock Tube Flows due to Unsteady Boundary Layer Action”, NACA TN 4021, 1957.
5.
MirelsH., “Flow Non-Uniformity in Shock Tubes Operating at Maximum Test Times”, Phys. Fluids19669, 1907.
6.
MartinW.A., “An Experimental Study of the Boundary Layer Behind a Moving Plane Shock Wave”, U.T.I.A.S. 1957 (Report No. 47).
7.
GooderumP.B., “An experimental Study of the Turbulent Boundary Layer on a Shock Tube Wall”, NACA TN 4243, 1958.
8.
ChenC.J.EmrichR.J., “Investigation of the Shock Tube Boundary Layer by a Tracer Method”, Phys. Fluids19636, 1.
9.
GionE.J., “Measured Velocity Profiles in the Laminar Boundary Layer Behind a Shock”, Phys. Fluids19658, 546.
10.
DosanjhD.S.KovásznayL.S.G.ClarkenP.C., “Study of Transient Hot Wire Response in a Shock Tube”, John Hopkins University, Dept. of Aeronautics1952 (Report No. CM725).
11.
ChristiansenW.H., “On the Use of Fine Unheated Wires in Shock Tubes”, Phys. Fluids19603, 1027.
12.
GudeK.E.ChristoffersenJ. Aa., “The Shock Front Curvature in a Shock Tube Measured with Hot-wire Anemometers”, DISA1968 (Information No. 6), 11.
13.
CollisD.C.WilliamsM.J., “Two-Dimensional Convection from Heated Wires at Low Reynolds Numbers”, J. Fluid Mech.19596, 357.
14.
LaurenceJ.C.SandbornV.A., “Heat transfer from Cylinders”, ASME Symp. on Measurement in Unsteady Flow 1962, 36.
15.
DönchF., “Turbulent Flow in Slightly Divergent and Convergent Channels”, Forschungsarbeiten V.D.I. 282.
16.
EmrichR.J.WheelerD.B., “Wall Effects in Shock Tube Flow”, Phys. Fluids19581, 14.
17.
Van DriestE.R., “Turbulent Boundary Layer in Compressible Fluids”, J. Aeronautical Sci.195118, 145.
18.
ArttD.W.BrownA., “The Simultaneous Measurement of Velocity and Temperature”, J. Phys. E., Sci. Instruments19714, 72.
