Numerical Study of Aerodynamic Characteristics of a Symmetric NACA Section with Simulated Ice Shapes. Issue 2 (September 2016)

• Record Type: Journal Article
• Authors: Tabatabaei, N.; Cervantes, M.J.; Trivedi, C.; Aidanpää, Jan-Olof
• Is Part Of: Journal of physics. Volume 753:Issue 2(2016)
• Publication Date: 2016-09
• Subjects: Physics -- Congresses; 530.5
• DOI: 10.1088/1742-6596/753/2/022055
• Languages: English
• ISSNs: 1742-6588

Abstract

Abstract: To develop a numerical model of icing on wind turbine blades, a CFD simulation was conducted to investigate the effect of critical ice accretions on the aerodynamic characteristics of a 0.610 m chord NACA 0011 airfoil section. Aerodynamic performance coefficients and pressure profile were calculated and compared with the available measurements for a chord Reynolds number of 1.83x106. Ice shapes were simulated with flat plates (spoiler-ice) extending along the span of the wing. Lift, drag, and pressure coefficients were calculated in zero angle of attack through the steady state and transient simulations. Different approaches of numerical studies have been applied to investigate the icing conditions on the blades. The simulated separated flow over the sharp spoilers is challenging and can be seen as a worst test case for validation. It allows determining a reliable strategy to simulate real ice shapes [1] for which the detailed validation cannot easily be provided.