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Research Papers: Fundamental Issues and Canonical Flows

# Experimental and Numerical Study of Laminar Round Jet Flows Along a Wall

[+] Author and Article Information
K. F. K. Adane, M. F. Tachie

Department of Mechanical and Manufacturing, University of Manitoba, Winnipeg, MB, R3T 5V6, Canada

J. Fluids Eng 132(10), 101203 (Oct 21, 2010) (10 pages) doi:10.1115/1.4002653 History: Received July 30, 2009; Revised September 17, 2010; Published October 21, 2010; Online October 21, 2010

## Abstract

In the present study, both experimental and numerical techniques were employed to study three-dimensional laminar wall jet flows. The wall jet was created using a circular pipe of diameter $7×10−3 m$ and flows into an open water tank. The inlet Reynolds numbers based on the pipe diameter and jet exit velocity were 310 and 800. A particle image velocimetry (PIV) was used to conduct detailed measurements at various streamwise-transverse and streamwise-spanwise planes. The complete nonlinear incompressible Navier–Stokes equation was also solved using a collocated finite volume based in-house computational fluid dynamics (CFD) code. The computation was performed for three inlet Reynolds numbers, namely, 310, 420, and 800. From the PIV measurements and CFD results, velocity profiles and jet half-widths were extracted at selected downstream locations. It was observed that the numerical results are in reasonable agreement with the experimental data. The distributions of the velocities, jet spread rates, and vorticity were used to provide insight into the characteristics of three-dimensional laminar wall jet flows.

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## Figures

Figure 1

Nomenclature of the present flow geometry

Figure 2

Schematic of the experimental setup

Figure 10

Comparison of normalized streamwise velocity gradient at X=10 and 20

Figure 11

Streamwise vorticity contours at [(a), (c), and (e)] Rej=310 and [(b), (d), and (f)] 800 for X=5, 30, and 60, respectively

Figure 5

Variation of (a) maximum velocity decay um and (b) local momentum flux. (c) and (d) are jet-half-widths in downstream direction. The dash lines are line of best fit to the experimental data.

Figure 8

Streamwise velocity (U) contours and secondary flow vectors (W, V): [(a), (c), and (e)] Rej=310 and [(b), (d), and (f)] 800 for X=5, 30, and 60. Note: first row is X=5, whereas last row is for X=60. Each contour level is 0.1 with maximum and minimum of 1.0 and 0.1, respectively.

Figure 9

Normalized spanwise vorticity contours in the regions: [(a) and (b)] 8≤X≤12 and [(c) and (d)] 20≤X≤24 at Rej=800. [(a) and (c)] For PIV and [(b) and (d)] for CFD.

Figure 3

Schematic of the present computational flow domain with boundary conditions

Figure 4

Velocity vectors in the regions: [(a) and (b)] 2≤X≤6, [(c) and (d)] 14≤X≤20, and (e) 34≤X≤40. [(a) and (c)] at Rej=310 and [(b), (d), and (e)] at Rej=800.

Figure 6

Variation of the spread rates at various Rej: transverse Sz and spanwise Sy [(a) and (b)] in downstream direction and [(e) and (f)] with local Reynolds number Rem, respectively. Variation of (c) the spread rate ratio and the local (d) Reynolds number Rem. The dash lines are for experimental data computed from the line of best fit.

Figure 7

Normalized streamwise velocity profiles on [(a), (c), and (e)] transverse and [(b), (d), and (f)] spanwise directions at various downstream locations

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