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Mathematical Problems in Engineering
Volume 2015 (2015), Article ID 854308, 31 pages
http://dx.doi.org/10.1155/2015/854308
Research Article

An Extended Assessment of Fluid Flow Models for the Prediction of Two-Dimensional Steady-State Airfoil Aerodynamics

1Wind Energy Group, Department of Physics, Instituto Tecnológico y de Estudios Superiores de Monterrey, Eugenio Garza Sada 2501 Sur, 64849 Monterrey, NL, Mexico
2Solar Energy and Thermosciences Group, Department of Mechanical Engineering, Instituto Tecnológico y de Estudios Superiores de Monterrey, Eugenio Garza Sada 2501 Sur, 64849 Monterrey, NL, Mexico
3Department of Mechanical Engineering, The University of Texas at San Antonio, One UTSA Circle, San Antonio, TX 78249, USA
4School of Mechanical and Electrical Engineering, Universidad Autónoma de Nuevo León, Avenida Universidad s/n, Ciudad Universitaria, 66451 San Nicolás de los Garza, NL, Mexico

Received 30 August 2014; Revised 13 January 2015; Accepted 13 January 2015

Academic Editor: Shaofan Li

Copyright © 2015 José F. Herbert-Acero et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Abstract

This work presents the analysis, application, and comparison of thirteen fluid flow models in the prediction of two-dimensional airfoil aerodynamics, considering laminar and turbulent subsonic inflow conditions. Diverse sensitivity analyses of different free parameters (e.g., the domain topology and its discretization, the flow model, and the solution method together with its convergence mechanisms) revealed important effects on the simulations’ outcomes. The NACA 4412 airfoil was considered throughout the work and the computational predictions were compared with experiments conducted under a wide range of Reynolds numbers () and angles-of-attack (). Improvements both in modeling accuracy and processing time were achieved by considering the RS LP-S and the Transition SST turbulence models, and by considering finite volume-based solution methods with preconditioned systems, respectively. The RS LP-S model provided the best lift force predictions due to the adequate modeling of the micro and macro anisotropic turbulence at the airfoil’s surface and at the nearby flow field, which in turn allowed the adequate prediction of stall conditions. The Transition-SST model provided the best drag force predictions due to adequate modeling of the laminar-to-turbulent flow transition and the surface shear stresses. Conclusions, recommendations, and a comprehensive research agenda are presented based on validated computational results.