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Boundary Layer Transition Induced by a Von Karman Vortex Street Wake
- Source :
- Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering. 210:167-179
- Publication Year :
- 1996
- Publisher :
- SAGE Publications, 1996.
-
Abstract
- A study has been made of the process of laminar to turbulent transition induced by a von Karman vortex street wake, in the boundary layer on a flat plate. The boundary layer developed under zero pressure gradient conditions while the vortex street was generated by a cylinder positioned in the free stream. Hot-wire measurements over a range of Strouhal frequencies and free stream velocities were used for the identification of the transition onset. From the analysis of the experimental data, two different transition mechanisms known in the literature as ‘strong’ wake and ‘weak’ wake induced transition, could be identified. It was established that, the onset of the strong von Karman wake induced transition process was a function of the free stream velocity, the position of the cylinder with respect to the plate, the cylinder diameter, the drag coefficient and the minimum velocity in the developing wake at the streamwise position of the onset of the boundary layer transition. The end of the strong wake induced transition, was defined at the streamwise distance, where the wake of the cylinder met the wall. A correlation for the prediction of the onset of the transition was developed
- Subjects :
- Physics
020301 aerospace & aeronautics
0209 industrial biotechnology
Mechanical Engineering
Aerospace Engineering
Laminar flow
02 engineering and technology
Mechanics
Wake
Boundary layer thickness
Kármán vortex street
Vortex
Physics::Fluid Dynamics
Boundary layer
020901 industrial engineering & automation
Classical mechanics
0203 mechanical engineering
Wake turbulence
Pressure gradient
Subjects
Details
- ISSN :
- 20413025 and 09544100
- Volume :
- 210
- Database :
- OpenAIRE
- Journal :
- Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering
- Accession number :
- edsair.doi...........7a3dd92ff23c88d5f449a7ff9f23c8b7
- Full Text :
- https://doi.org/10.1243/pime_proc_1996_210_358_02