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The effects of wake splitter plates on the flow past a circular cylinder in the range 104<R4

  • C. J. Apelt (a1), G. S. West (a1) and Albin A. Szewczyk (a2)
Abstract

Experiments were carried out using models having L/D [les ] 2 and the resulting pressure distributions and vortex shedding characteristics are presented. A simple visualization technique which provides explanations of some of the measured results is described. It is concluded that splitter planes reduce the drag markedly by stabilizing the separation points and produce a wake narrower than that for a plain cylinder, raise the base pressure by as much as 50% and affect the Strouhal number to a lesser degree. Careful measurement techniques have enabled these effects to be presented accurately.

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References
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Apelt, C. J. & Isaacs, L. T. 1970 Effects of splitter plates placed in the wake of bluff cylinders. C.A.A.R.C. Symp. on Separated Flows and Wakes, University of Melbourne.
Bearman, P. W. 1965 Investigation of the flow behind a two-dimensional model with a blunt trailing edge and fitted with splitter plates. J. Fluid Mech. 21, 241.
Gerrard, J. H. 1965 The mechanics of the formation region of vortices behind bluff bodies. J. Fluid Mech. 25, 401.
Lienhard, J. H. 1966 Synopsis of lift, drag, and vortex frequency data for rigid circular cylinders. Wash. State University Bull. no. 300.
Maskell, E. C. 1963 A theory of the blockage effects on bluff bodies and stalled wings in a closed wind tunnel. Aero. Res. Counc. R & M. no. 3400.
Roshko, A. 1954 On the drag and shedding frequency of two-dimensional bluff bodies. N.A.C.A. Tech. Note, no. 3169.
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Journal of Fluid Mechanics
  • ISSN: 0022-1120
  • EISSN: 1469-7645
  • URL: /core/journals/journal-of-fluid-mechanics
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