0
Gas Turbines: Turbomachinery

Aerodynamic Improvements of Wind-Turbine Airfoil Geometries With the Prescribed Surface Curvature Distribution Blade Design (CIRCLE) Method

[+] Author and Article Information
T. Korakianitis1

M. A. Rezaienia, I. A. Hamakhan, E. J. Avital, J. J. R. Williams

 School of Engineering and Materials Science, Queen Mary University of London,London, E1 4NS, United Kingdom

1

Corresponding author.

J. Eng. Gas Turbines Power 134(8), 082601 (Jun 19, 2012) (9 pages) doi:10.1115/1.4005969 History: Received July 11, 2011; Revised August 09, 2011; Published June 19, 2012; Online June 19, 2012

The prescribed surface curvature distribution blade design (CIRCLE) method can be used for the design of two-dimensional (2D) and three-dimensional (3D) turbomachinery blade rows with continuous curvature and slope of curvature from leading edge (LE) stagnation point to trailing edge (TE) stagnation point and back to the LE stagnation point. This feature results in smooth surface pressure distribution airfoils with inherently good aerodynamic performance. In this paper the CIRCLE blade design method is modified for the design of 2D isolated airfoils. As an illustration of the capabilities of the method, it is applied to the redesign of two representative airfoils used in wind turbine blades: the Eppler 387 airfoil and the NREL S814 airfoil. Computational fluid dynamic analysis is used to investigate the design point and off-design performance of the original and modified airfoils, and compare with experiments on the original ones. The computed aerodynamic advantages of the modified airfoils are discussed. The surface pressure distributions, drag coefficients, and lift-to-drag coefficients of the original and redesigned airfoils are examined. It is concluded that the method can be used for the design of wind turbine blade geometries of superior aerodynamic performance.

FIGURES IN THIS ARTICLE
<>
Copyright © 2012 by American Society of Mechanical Engineers
Your Session has timed out. Please sign back in to continue.

References

Figures

Grahic Jump Location
Figure 1

Effect of Reynolds number and surface roughness on airfoil CL /CD (adapted from [24])

Grahic Jump Location
Figure 2

Good and bad boundary layers on airfoil

Grahic Jump Location
Figure 3

Curvature C (defined by Eq. 1) and y, or y ′ or y ″ continuity are not similar quantities

Grahic Jump Location
Figure 4

2D blade and airfoil geometry definition (adapted from [30,34])

Grahic Jump Location
Figure 5

Comparison of Eppler 387, A1, and A2 airfoils

Grahic Jump Location
Figure 6

Comparison of NREL S814 and R1 airfoils

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