FENSAP-ICE Simulation of Icing on Wind Turbine Blades, Part 1: Performance Degradation

Reid, Thomas; Baruzzi, Guido S.; Ozcer, Isik; Switchenko, David; Habashi, Wagdi G.

doi:10.2514/6.2013-750

Cited by 24 publications

(23 citation statements)

References 19 publications

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“…The aerodynamic performance degradation due to icing was simulated with FENSAP, a state-of-the-art Navier-Stokes CFD solver [42]. The solver is part of the software package ANSYS FENSAP-ICE (version 19.2) [43], which is a second generation icing simulation tool suitable for a wide range of applications but with limited published validation data-in particular, for low Reynolds numbers. One objective of this study was to use FENSAP as an example to compare it to the experimental dataset and assess its capability to capture icing performance penalties at low Reynolds numbers.…”

Section: Methodsmentioning

confidence: 99%

Experimental and Numerical Icing Penalties of an S826 Airfoil at Low Reynolds Numbers

et al. 2020

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Most icing research focuses on the high Reynolds number regime and manned aviation. Information on icing at low Reynolds numbers, as it is encountered by wind turbines and unmanned aerial vehicles, is less available, and few experimental datasets exist that can be used for validation of numerical tools. This study investigated the aerodynamic performance degradation on an S826 airfoil with 3D-printed ice shapes at Reynolds numbers Re = 2 × 105, 4 × 105, and 6 × 105. Three ice geometries were obtained from icing wind tunnel experiments, and an additional three geometries were generated with LEWICE. Experimental measurements of lift, drag, and pressure on the clean and iced airfoils have been conducted in the low-speed wind tunnel at the Norwegian University of Science and Technology. The results showed that the icing performance penalty correlated to the complexity of the ice geometry. The experimental data were compared to computational fluid dynamics (CFD) simulations with the RANS solver FENSAP. Simulations were performed with two turbulence models (Spalart Allmaras and Menter’s k-ω SST). The simulation data showed good fidelity for the clean and streamlined icing cases but had limitations for complex ice shapes and stall.

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Section: Methodsmentioning

confidence: 99%

Experimental and Numerical Icing Penalties of an S826 Airfoil at Low Reynolds Numbers

et al. 2020

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“…9 American Institute of Aeronautics and Astronautics The closer agreement between computation and experiment at the higher Reynolds number and Mach number also indicate that accurate simulation of the viscous region plays a role in the overall computation. As the angle of attack increases, the difference between the computation and experiment increases.…”

Section: Resultsmentioning

confidence: 71%

Computational Aerodynamic Analysis of Three-dimensional Ice Shapes on a NACA 23012 Airfoil

Jun

Oliden

Potapczuk

et al. 2014

6th AIAA Atmospheric and Space Environments Conference

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The present study identifies a process for performing computational fluid dynamic calculations of the flow over full three-dimensional (3D) representations of complex ice shapes deposited on aircraft surfaces. Rime and glaze icing geometries formed on a NACA23012 airfoil model were obtained during testing in the NASA Glenn Research Center's Icing Research Tunnel (IRT). The ice shape geometries were scanned as a cloud of data points using a 3D laser scanner. The data point clouds were meshed using Geomagic software to create highly accurate models of the ice surface. The surface data was imported into Pointwise grid generation software to create the CFD surface and volume grids. It was determined that generating grids in Pointwise for complex 3D icing geometries was possible using various techniques that depended on the ice shape. Computations of the flow fields over these ice shapes were performed using the NASA National Combustion Code (NCC). Results for a rime ice shape for angle of attack conditions ranging from 0 to 10 degrees and for freestream Mach numbers of 0.10 and 0.18 are presented. For validation of the computational results, comparisons were made to test results from rapid-prototype models of the selected ice accretion shapes, obtained from a separate study in a subsonic wind tunnel at the University of Illinois at Urbana-Champaign. The computational and experimental results were compared for values of pressure coefficient and lift. Initial results show fairly good agreement for rime ice accretion simulations across the range of conditions examined. The glaze ice results are promising but require some further examination. NomenclatureAOA = Angle of Attack CFD = Computational Fluid Dynamics NCC = National Combustion Code C f = skin friction Re s = Reynolds number based on distance along the surface U ∞ = free stream velocity * = friction velocity

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“…In another work (Buschhorn et al 2013), the application of conductive polymer nanocomposites in making highly efficient electro-thermal IPS was tested under a range of icing conditions. In (Reid et al 2013a(Reid et al , 2013b, numerical approaches to performance degradation analysis and to provide guidelines for the design of wind turbine electro-thermal anti-icing systems, are presented. Clean Sky, an aeronautical research program in Europe, has recently launched a project on the combination of smart coatings with electro-thermal systems to minimize the runback ice over natural laminar flow wings' surfaces.…”

Section: Introductionmentioning

confidence: 99%

Constrained problem formulations for power optimization of aircraft electro-thermal anti-icing systems

et al. 2015

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Various constrained problem formulations for the optimization of an electro-thermal wing anti-icing system in both running-wet and evaporative regimes are presented. The numerical simulation of the system is performed by solving the conjugate heat transfer problem between the fluid and solid domains. The optimization goal is to reduce the energy use and power demand of the anti-icing system while ensuring a safe protection. The formulations are carefully proposed from the physical and mathematical viewpoints; their performance is assessed by means of several numerical test cases to discern the most promising for each regime. The design optimization is conducted using the mesh adaptive direct search algorithm using quadratic and statistical surrogate models in the search step. The influence of the models on the convergence speed and the quality of the obtained design solutions is investigated.

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FENSAP-ICE Simulation of Icing on Wind Turbine Blades, Part 1: Performance Degradation

Cited by 24 publications

References 19 publications

Experimental and Numerical Icing Penalties of an S826 Airfoil at Low Reynolds Numbers

Experimental and Numerical Icing Penalties of an S826 Airfoil at Low Reynolds Numbers

Computational Aerodynamic Analysis of Three-dimensional Ice Shapes on a NACA 23012 Airfoil

Constrained problem formulations for power optimization of aircraft electro-thermal anti-icing systems

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