The purpose of this paper is to study the effect of a porous, compliant, anisotropic coating on the fluid-dynamical performance of a NACA0012 airfoil, under conditions of boundary-layer separation. This fluid-structure interaction problem is studied computationally in two dimensions by performing a detailed parametric study of the coating, with respect to its physical dimensions, characteristics and placement on the airfoil. Aerodynamic performances are quantified in terms of the non-dimensional mean drag and lift coefficients. The configuration described here is a separated flow at Re = 1100 and α = 70°. Coating parameters are found which decrease the amplitude of the drag oscillations by about 11% and increase the mean lift by about 9%. © 2010 International Federation for Medical and Biological Engineering.
CITATION STYLE
Venkataraman, D., & Bottaro, A. (2010). Flow separation control on a NACA0012 airfoil via a porous, compliant coating. In IFMBE Proceedings (Vol. 31 IFMBE, pp. 52–55). https://doi.org/10.1007/978-3-642-14515-5_14
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