Secondary instability of a swept-wing boundary layer disturbed by controlled roughness elements
Journal article, 2010

Wind-tunnel data on velocity perturbations evolving in a laminar swept-wing flow under low subsonic conditions are reported. The focus of the present experiments are secondary disturbances of the boundary layer which is modulated by stationary streamwise vortices. Both the stationary vortices and the secondary oscillations of interest are generated in a controlled manner. The experimental data are obtained through hot-wire measurements. Thus, evolution of the vortices, either isolated or interacting with each other, is reconstructed in detail. As is found, the secondary disturbances, initiating the laminar-flow breakdown, are strongly affected by configuration of the stationary boundary-layer perturbation that may have an implication to laminar-turbulent transition control.

Transition

cross-flow vortices

control

Streamwise vortices

Swept wing

stability

Secondary instabilities

growth

transition

Author

Valery Chernoray

Chalmers, Applied Mechanics, Fluid Dynamics

A. V. Dovgal

Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the RAS

V. V. Kozlov

Khristianovich Institute of Theoretical and Applied Mechanics of the Siberian Branch of the RAS

Lennart Löfdahl

Chalmers, Applied Mechanics, Vehicle Safety

Journal of Visualization

1343-8875 (ISSN) 1386-6478 (eISSN)

Vol. 13 3 251-256

Subject Categories

Mechanical Engineering

DOI

10.1007/s12650-010-0035-0

More information

Created

10/8/2017