0
Research Papers

Trailing Edge Noise Model Validation and Application to Airfoil Optimization

[+] Author and Article Information
F. Bertagnolio1

Wind Energy Division, Risø National Laboratory for Sustainable Energy, Technical University of Denmark (DTU), P.O. Box 49, Roskilde DK-4000, Denmarkfrba@risoe.dtu.dk

H. Aa. Madsen

Wind Energy Division, Risø National Laboratory for Sustainable Energy, Technical University of Denmark (DTU), P.O. Box 49, Roskilde DK-4000, Denmarkhama@risoe.dtu.dk

C. Bak

Wind Energy Division, Risø National Laboratory for Sustainable Energy, Technical University of Denmark (DTU), P.O. Box 49, Roskilde DK-4000, Denmarkchba@risoe.dtu.dk

1

Corresponding author.

J. Sol. Energy Eng 132(3), 031010 (Jun 21, 2010) (9 pages) doi:10.1115/1.4001462 History: Received June 08, 2009; Revised December 21, 2009; Published June 21, 2010; Online June 21, 2010

The aim of this article is twofold. First, an existing trailing edge noise model is validated by comparing with airfoil surface pressure fluctuations and far field sound pressure levels measured in three different experiments. The agreement is satisfactory in one case but poor in two other cases. Nevertheless, the model reproduces the main tendencies observed in the measurements with respect to varying flow conditions. Second, the model is implemented into an airfoil design code that is originally used for aerodynamic optimization. An existing wind turbine airfoil is optimized in order to reduce its noise emission, trying at the same time to preserve some of its aerodynamic and geometric characteristics. The new designs are characterized by less cambered airfoils and flatter suction sides. The resulting noise reductions seem to be mainly achieved by a reduction in the turbulent kinetic energy across the boundary layer near the trailing edge and to a lesser extent by a smaller boundary layer displacement thickness.

FIGURES IN THIS ARTICLE
<>
Copyright © 2010 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Surface pressure spectra on NACA0015 airfoil at x/C=0.567

Grahic Jump Location
Figure 2

Surface pressure spectra on NACA0012 airfoil (lines: experiment (14); lines with circles: TNO model)

Grahic Jump Location
Figure 3

Far field SPL for NACA0012 airfoil (lines: U=38.6 m/s; lines with crosses: U=56.5 m/s)

Grahic Jump Location
Figure 4

Far field SPL for NACA0012 airfoil (lines: AWB experiment (20); lines with circles: TNO model)

Grahic Jump Location
Figure 5

Airfoil shape and displacement thickness along airfoil suction side

Grahic Jump Location
Figure 6

Aerodynamic characteristics

Grahic Jump Location
Figure 7

Far field noise—α=8 deg

Grahic Jump Location
Figure 8

Boundary layer characteristics near trailing edge on the suction side—α=8 deg

Grahic Jump Location
Figure 9

Verification of design using CFD—α=8 deg

Tables

Errata

Discussions

Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In