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A vertically oscillating plate disturbing the development of a boundary layer

Published online by Cambridge University Press:  26 April 2006

J. J. Miau
Affiliation:
Institute of Aeronautics and Astronautics, National Cheng Kung University, Tainan, Taiwan, Republic of China
C. R. Chen
Affiliation:
Institute of Aeronautics and Astronautics, National Cheng Kung University, Tainan, Taiwan, Republic of China
J. H. Chou
Affiliation:
Department of Engineering Science, National Cheng Kung University, Tainan, Taiwan, Republic of China

Abstract

A vertically oscillating plate in a boundary layer regulates the vorticity flux rate with respect to time and displaces the vorticity away from the wall. These phenomena are discussed for non-dimensional frequencies of the oscillating plate K = 0, 0.006, 0.01 and 0.02. The velocity data obtained by a split-fibre probe near the wall in the region immediately downstream of the oscillating plate lead to a discussion on the behaviour of the flow structures with respect to the non-dimensional frequency. The physical understanding deduced is complementary to the findings of a smoke-wire flow visualization conducted in this study. An integral analysis of the momentum equation indicates that the mean vorticity flux rate of the present flow is composed of contributions from both the parallel shear layer and the curving streamline. This analysis further suggests that the mean vorticity flux rate can be obtained through a combination of pressure measurements at the wall and in the irrotational region of the flow.

Type
Research Article
Copyright
© 1995 Cambridge University Press

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References

Chen, C. R. 1991 Effects of a two-dimensional oscillating fence on boundary-layer development. 1 thesis, Institute of Aeronautics and Astronautics, National Chen Kung University, Tainan, Taiwan.
Doligalski, T. L. & Walker, J. D. A. 1984 The boundary layer induced by a convected two- dimesional vortex. J. Fluid Mech. 139, 128.Google Scholar
Eaton, J. K. & Johnston, J. P. 1982 Low frequency unsteadiness of a reattaching turbulent shear layer. In Turbulent Shear Flows 3 (ed. L. J. S. Bradbury, F. Durst, B. E. Launder, F. W. Schmidt & J. H. Whitelaw), pp. 162170. Springer.
Francis, M. S., Keesee, J. E., Lang, J. D., Sparks, G. W. & Sisson, G. E. 1979 Aerodynamic characteristics of an unsteady separation flow. AIAA J. 17, 13321339.Google Scholar
Kiya, M. & Sasaki, K. 1983 Structure of a turbulent separation bubble. J. Fluid Mech. 137, 83113.Google Scholar
Kiya, M. & Sasaki, K. 1985 Structure of large-scale vortices and unsteady reverse flow in the reattaching zone of a turbulent separation bubble. J. Fluid Mech. 154, 463491.Google Scholar
Koga, D. J. 1983 Control of separated flow fields using forced unsteadiness. PhD thesis, Illinois Inst. of Technology.
Miau, J. J., & Chen, M. H. 1991 Flow structures behind a vertically oscillating fence immersed in a flat-plate turbulent boundary layer. Exps. Fluids 11, 118124.Google Scholar
Miau, J. J., Chen, M. H. & Chou, J. H. 1991a Frequency effect of an oscillating plate immersed in a turbulent boundary layer. AIAA J. 29, 10681074.Google Scholar
Miau, J. J., Lee, K. C., Chen, M. H. & Chou, J. H. 1991b Control of separated flow by a two-dimensional oscillating fence. AIAA J. 29, 11401148.Google Scholar
Nagib, H. M., Reisenthel, P. H. & Koga, D. J. 1985 On the dynamical scaling of forced unsteady separated flows. AIAA Paper 85-0553.
Reisenthel, P. H., Nagib, H. M. & Koga, D. J. 1985 Control of separated flows using forced unsteadiness. AIAA Paper 85-0556.
Reynolds, W. C. & Carr, L. W. 1985 Review of unsteady, driven, separated flows. AIAA Paper 85-0527.
Sears, W. R. 1956 Some recent developments in airfoil theory. J. Aero. Sci. 23, 490499.Google Scholar