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Research Papers: Flows in Complex Systems

Influence of Staggering Angle of a Rotating Rod on Flow Past a Circular Cylinder

[+] Author and Article Information
T. Ayyappan

Department of Applied Mechanics, IIT Madras, Chennai 600036, India

S. Vengadesan1

Department of Applied Mechanics, IIT Madras, Chennai 600036, Indiavengades@iitm.ac.in

1

Corresponding author.

J. Fluids Eng 130(3), 031103 (Mar 03, 2008) (11 pages) doi:10.1115/1.2842224 History: Received January 22, 2007; Revised October 27, 2007; Published March 03, 2008

The influence of the staggering position of a rotating rod on flow past a main circular cylinder is investigated numerically. The rod is rotated at a constant speed ratio of 3. The effect of the diameter ratio of the rotating rod is studied by considering two different diameter ratios. The investigation is carried out at a fixed pitch length of 1. The study is carried out for two Reynolds number, viz., 100 and 500. The momentum injection from the rod is found to alter the flow characteristics behind the main cylinder. For a certain arrangement of stagger angle and diameter ratio, the vortex shedding behind the main cylinder gets suppressed. The corresponding configuration for which minimum drag coefficient is achieved is suggested from this study.

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Copyright © 2008 by American Society of Mechanical Engineers
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Figures

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Figure 1

Typical grid used for flow over an isolated circular cylinder. (a) Complete domain. (b) Enlarged view of the grid near the cylinder.

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Figure 2

Schematic arrangement of the present study

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Figure 3

Results for the isolated rotating cylinder. Legends are the same in both plots. (a) Variation of mean lift coefficient. (b) Variation of mean drag coefficient. (c) Variation of wall pressure coefficient with speed ratio.

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Figure 4

Variation of aerodynamic coefficients. (a) Mean drag coefficient of the main cylinder. (b) Mean lift coefficient of the main cylinder. (c) rms lift coefficient of the main cylinder. (d) Mean drag coefficient of the rod. Legends are the same in all plots.

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Figure 5

Mean streamline contours for d∕D=0.5. (a) Tandem arrangement. (b) Staggering angle of 10deg.

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Figure 6

(a) Instantaneous vorticity contour for d∕D=0.2 and α=90deg: (i) ω=0 and (ii) ω=3. (b) Instantaneous vorticity contour for d∕D=0.5 and α=45deg: (i) ω=0 and (ii) ω=3. (c) Instantaneous vorticity contour for d∕D=0.5 and α=90deg: (i) ω=0 and (ii) ω=3.

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Figure 7

urms contour for (a) d∕D=0.5, α=0deg, and ω=0 and (b) d∕D=0.5, α=0deg, and ω=3

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Figure 8

Mean streamwise velocity along the wake centerline for (a) d∕D=0.2 and (b) d∕D=0.5. Legends are the same in both plots.

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Figure 9

(a) Variation of mean streamwise velocity along a normal line at x1∕D=0 for Re=100 and d∕D=0.2. (b) Variation of mean streamwise velocity along a normal line at x1∕D=0 for Re=100 and d∕D=0.5. Legends are the same in both plots.

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Figure 10

Contours of streamwise vorticity for the case of d∕D=0.2 and ω=3. (a) α=0deg; (b) α=90deg.

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Figure 11

Variation of aerodynamic coefficients. (a) Mean drag coefficient of the main cylinder. (b) Mean lift coefficient of the main cylinder. (c) rms lift coefficient of the main cylinder. (d) Mean drag coefficient of the rod. Legends are the same in all plots.

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Figure 12

Variation of mean streamwise velocity along a normal line for d∕D=0.5 and Re=500. (a) x∕D=0; (b) x∕D=1. Legends are the same in both plots.

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Figure 13

Variation of system drag for both diameter ratios and Reynolds numbers

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