Flow past two in-tandem airfoils undergoing sinusoidal oscillations

Flow past two in-tandem airfoils undergoing sinusoidal oscillations The interaction of the wake, generated behind an upstream oscillating NACA 0012 airfoil, with the downstream NACA 0012 airfoil, oscillated at the same conditions but with ϕ = 0° and 180° different phases (relative to the upstream airfoil), was investigated by particle image velocimetry and surface pressure measurements. The results show that the axial spacing and phase difference determined the strength of the undesirable interference effects and, subsequently, the behavior of the dynamic-load loops of the downstream airfoil. The boundary-layer events on the downstream airfoil were persistently different from those observed on the baseline oscillating airfoil. The downwash induced by the upstream airfoil disrupted leading-edge vortex (LEV) formation on the downstream airfoil. The absence of LEV-induced transient effects also led to a significantly lowered aerodynamic loading and C l -hysteresis compared to the baseline airfoil. The aerodynamic performance of the ϕ = 180° case, however, outperformed that of the ϕ = 0° case. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Experiments in Fluids Springer Journals

Flow past two in-tandem airfoils undergoing sinusoidal oscillations

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Publisher
Springer-Verlag
Copyright
Copyright © 2011 by Springer-Verlag
Subject
Engineering; Engineering Thermodynamics, Heat and Mass Transfer; Engineering Fluid Dynamics; Fluid- and Aerodynamics
ISSN
0723-4864
eISSN
1432-1114
D.O.I.
10.1007/s00348-011-1173-4
Publisher site
See Article on Publisher Site

Abstract

The interaction of the wake, generated behind an upstream oscillating NACA 0012 airfoil, with the downstream NACA 0012 airfoil, oscillated at the same conditions but with ϕ = 0° and 180° different phases (relative to the upstream airfoil), was investigated by particle image velocimetry and surface pressure measurements. The results show that the axial spacing and phase difference determined the strength of the undesirable interference effects and, subsequently, the behavior of the dynamic-load loops of the downstream airfoil. The boundary-layer events on the downstream airfoil were persistently different from those observed on the baseline oscillating airfoil. The downwash induced by the upstream airfoil disrupted leading-edge vortex (LEV) formation on the downstream airfoil. The absence of LEV-induced transient effects also led to a significantly lowered aerodynamic loading and C l -hysteresis compared to the baseline airfoil. The aerodynamic performance of the ϕ = 180° case, however, outperformed that of the ϕ = 0° case.

Journal

Experiments in FluidsSpringer Journals

Published: Aug 4, 2011

References

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