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Effect of spanwise confinement on flag flutter: Experimental measurements
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10.1063/1.3662127
/content/aip/journal/pof2/23/11/10.1063/1.3662127
http://aip.metastore.ingenta.com/content/aip/journal/pof2/23/11/10.1063/1.3662127
View: Figures

Figures

Image of FIG. 1.
FIG. 1.

(Color online) Sketch view of the experimental setup: (a) top view, (b) side view, (c) side view with additionnal plexiglass plates and adhesive tapes to decrease the channel width.

Image of FIG. 2.
FIG. 2.

(Color online) Typical evolution of the rms level of the displacement, measured at an arbitrary point near the clamped end of the plate; (○) increasing velocity, () decreasing velocity, L = 86 mm (a), H = 15 mm, C = 12 mm; (b) H = 8 mm, C = 16 mm.

Image of FIG. 3.
FIG. 3.

(Color online) Evolution of the non-dimensional critical flow velocity for flutter instability U * as function of the aspect ratio h of the plate; (o) experimental data; (—) 3D c model; (–  –) 3D model; (…) 2D model (infinite span). The experimental value of c is plotted as reference above.

Image of FIG. 4.
FIG. 4.

(Color online) Evolution of the non-dimensional critical flow velocity for flutter instability U * as function of the non-dimensional gap c for three different plates. Plate 1: M * = 0.48, h = 0.16, (o), experiment; (– –) 3D c model. Plate 2: M * = 0.48, h = 0.2, () experiment; (– ·–·) 3D c model. Plate 3: M * = 0.53, h = 0.43, (Δ) experiment; (—) 3D c model. Thin lines indicate the values given by the 3D model, while the dotted line indicates the value given by the 2D model for M * = 0.5. Inset: U * − U 2 D plotted as function of cc in a log-log scale, showing that it is governed by a power law of the form c 0.15.

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/content/aip/journal/pof2/23/11/10.1063/1.3662127
2011-11-29
2014-04-19
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752b84549af89a08dbdd7fdb8b9568b5 journal.articlezxybnytfddd
Scitation: Effect of spanwise confinement on flag flutter: Experimental measurements
http://aip.metastore.ingenta.com/content/aip/journal/pof2/23/11/10.1063/1.3662127
10.1063/1.3662127
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