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- Publisher
- Springer Journals
- Copyright
- Copyright © 2014 by Springer-Verlag Berlin Heidelberg
- Subject
- Engineering; Engineering Fluid Dynamics; Fluid- and Aerodynamics; Engineering Thermodynamics, Heat and Mass Transfer
- ISSN
- 0723-4864
- eISSN
- 1432-1114
- DOI
- 10.1007/s00348-014-1811-8
- Publisher site
- See Article on Publisher Site
Abstract
The aerodynamic interaction of a stream-wise vortex impacting on a NACA 23012 oscillating airfoil was investigated using stereo particle image velocimetry. The experimental rig enabled the study of the aerodynamic effects due to the blade pitching motion in the interaction with the vortex. The experimental study focused on the light dynamic stall regime, which represents a typical condition of the retreating blade of a helicopter in forward flight. Particle image velocimetry was applied to a measurement volume close to the airfoil upper surface in order to obtain the three-dimensional interacting flow field. In particular, the experimental results show that during the airfoil downstroke motion, the vortex impact triggers the stall of the local blade section, indicating that detrimental effects on the blade performance can be introduced by perpendicular vortex interactions.
Journal
Experiments in Fluids – Springer Journals
Published: Aug 26, 2014