3D Ice Accretion Simulation for Complex Configuration Basing on Improved Messinger Model

Abstract:

Ice accretion on 3D complex configuration is studied by numerical methods. The flow field is obtained by using Fluent 6.0 with a S-A turbulence model. Droplet trajectories and impingement characteristics are obtained by using the Eulerian approach. Ice shape is calculated based on the improved Messinger model with a new runback distribution scheme. By applying the method presented in this paper, ice accretion on NACA0012 is computed and the results are in good agreement with the available experiment data. It preliminarily shows that the improved method in this paper is feasible, Meanwhile, ice accretion on a four-element wing is studied. According to the analysis of the calculated result, the method presented in the paper can correctly simulate the ice accretion on 3D complex configuration.

• Periodical: Advanced Materials Research (Volumes 1025-1026)
• Pages: 148-155
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.1025-1026.148
• Online since: September 2014
• Authors: Cheng Xiang Zhu*, Chun Ling Zhu, Bin Fu
• Keywords: Ice Accretion, Messinger Model, Multi-Element Airfoil, Numerical Simulation, Runback Distribution Scheme

References

[1] S. Weimin, J. Shengju and L. Fengwei: Icing Research for Airfoil and Multi-element Airfoil, 24th AIAA Applied Aerodynamics Conference, AIAA 2006-3647 (2006).

DOI: 10.2514/6.2006-3647

[2] C. Giulio, C.E. De and W.G. Habashi: FENSAP-ICE: Numerical Prediction of In-flight Icing Roughness Evolution, 1st AIAA Atmospheric and Space Enviroment Conference, AIAA 2009-4126 (2009).

DOI: 10.2514/6.2009-4126

[3] Z. Zhihong, L. Fengwei, L. Guangning, et al.: Icing Numerical Simulation for Single and Multi-Element Airfoils, 28th AIAA Applied Aerodynamics Conference, AIAA 2010-4232 (2010).

DOI: 10.2514/6.2010-4232

[4] A.R. Gary and M.B. Brian: Users manual for the NASA LEWICE ice accretion prediction code (LEWICE), NASA CR-185129 (1990).

DOI: 10.2514/6.1995-752

[5] T. Hedde and D. Guffond: Improvement of the ONERA 3D Icing Code, Comparison with 3D Experimental Shapes, AIAA 93-0169 (1993).

DOI: 10.2514/6.1993-169

[6] M.G. Potapczuk: Colin S Bidwell. Swept Wing Ice Accretion Modeling, AIAA-90-0756 (1990).

DOI: 10.2514/6.1990-756

[7] B.W. William: User Manual for the NASA Glenn Ice Accretion Code LEWICE: Version2. 2. 2. NASA/CR211793 (2002).

[8] Fluent 6. 0 User's Guide, Fluent Inc. (2001).

[9] Y. Bourgault, W.G. Habashi, J. Dompierre, et al.: An Eulerian Approach to supercooled Droplets Impingement Calculations, American Institute of Aeronautics and Astronautics (1997).

DOI: 10.2514/6.1997-176

[10] S. Wirogo and S. Srirambhatla: An Eulerian method to calculate the collection efficiency on two and three dimensional bodies, AIAA 2003-1073 (2003).

DOI: 10.2514/6.2003-1073

[11] E. Iuliano, V. Brandi, 0 G. Mingione: Water Impingment Prediction on Multi-Element Airfoils by Means of Eulerian and Lagrangian Approach with Viscous and Inviscid Air Flo, 44th AIAA Aerospace Sciences Meeting and Exhibit, AIAA 2006-1270 (2006).

DOI: 10.2514/6.2006-1270

[12] Z.L. Tong and E.A. Luke: Eulerian simulation of icing collection efficiency using a singularity diffusion model, AIAA 2005-12466 (2005).

DOI: 10.2514/6.2005-1246

[13] W.Q. Tao: Numerical Heat Transfer (Second Edition), Xi'an: Press of Xi'an Jiaotong University (2001).

[14] A. Rothmayer and J.W. Tsao: Film Runback on an Airfoil Surface, AIAA-2000-0237 (2000).

DOI: 10.2514/6.2000-237

[15] H.H. Chen and C. Tuncer: A Turbulence Model for Iced Airfoils and Its Validation, AIAA-92-0417 (1992).