This content is not included in your SAE MOBILUS subscription, or you are not logged in.
Comparison of Experimental and Computational Ice Shapes for a Swept Wing Model
ISSN: 0148-7191, e-ISSN: 2688-3627
Published June 13, 2011 by SAE International in United States
Annotation ability available
Two-dimensional and three-dimensional leading edge ice shapes for a finite wing model computed with the NASA Glenn LEWICE 2.0 and LEWICE3D Version 2 ice accretion codes are compared with experimental data from icing tunnel tests. The wing model had 28° leading edge sweep angle, 1.52-m (60-in) semispan and an airfoil section representative of business jet wings. Experimental wing leading edge ice shapes were obtained at the NASA Glenn Icing Research Tunnel (IRT) for six icing conditions. Tests conditions included angles of attack of 4° and 6°, airspeeds ranging from 67.06 m/s (150 mph) to 111.76 m/s (250 mph), static air temperatures in the range of -11.28°C (11.7°F) to -2.78°C (27°F), liquid water contents of 0.46 g/m₃, 0.51 g/m₃, and 0.68 g/m₃, and median volumetric diameters of 14.5 μm and 20 μm. In the experimental investigation, four glaze ice shapes with complete scallop features were obtained using progressively longer ice accretion times (2, 5, 10, and 22.5 minutes) to provide a range of horn sizes. Also, a 10-min incomplete scallop glaze ice shape, a 22.5-min glaze ice accretion representative of an ice protection system failure case, and a 5-min rime ice shape were generated. Aerodynamic and icing analyses were performed for the six cases investigated during the icing tunnel tests. Generally, the analytical ice shapes were observed to have greater vertical extents between the ice horns and smaller ice growth in the chordwise direction than their experimental counterparts.
CitationWong, S., Papadakis, M., Yeong, H., and Wong, S., "Comparison of Experimental and Computational Ice Shapes for a Swept Wing Model," SAE Technical Paper 2011-38-0093, 2011, https://doi.org/10.4271/2011-38-0093.
- SAE International Aerospace Recommended Practice “Droplet Impingement and Ice Accretion Computer Codes,” SAE Standard ARP5903 October 2003
- AGARD (Advisory Group for Aerospace Research & Development) “Ice Accretion Simulation Evaluation Test,” AGARD-RTOTR-038 November 2001
- Wright, W. B. “Validation Results for LEWICE 3.0,” NASA/CR-2005-213561 March 2005
- Wright, W. B. Rutkowski, A. “Validation Results for LEWICE 2.0,” NASA/CR-1999-207690 January 1999
- Wright, W. B. Potapczuk, M. G. “Comparison of LEWICE 1.6 and LEWICE/NS with IRT Experimental Data from Modern Airfoil Tests,” AIAA 1997-0175, 35 th AIAA Aerospace Sciences Meeting and Exhibit Reno, Nevada January 1997
- Wright, W. B. “User Manual for the NASA Glenn Ice Accretion Code LEWICE (Version 2.0),” NASA CR-1999-209409 September 1999
- Bidwell, C. S. “Users Manual for the NASA Glenn Three-Dimensional Grid Based Ice Accretion Code (LEWI3DGR Ver. 1.7),” February 2005
- Vargas, M. Papadakis, M. Potapczuk, M. Addy, H. Sheldon, D. Giriunas, J. “Ice Accretions on a Swept GLC-305 Airfoil,” SAE Technical Paper 2002-01-1519 2002 10.4271/2002-01-1519
- Papadakis, M. Yeong, H. W. Wong, S. C. Vargas, M. Potapczuk, M. “Experimental Investigation of Ice Accretion Effects on a Swept Wing,” DOT/FAA/AR-05/39 August 2005
- Addy, H. “Ice Accretions and Icing Effects for Modern Airfoils,” DOT/FAA/AR-99/89, NASA TP-2000-210031 April 2000
- FLUENT 12.1.4 User's Guide ANSYS Inc. 2009
- ANSYS ICEM CFD 12.1, User's Guide SAS IP, Inc. 2009
- Papadakis, M. Yeong, H. W. Wong, S. C. Wong, S. H. “Comparison of Experimental and Computational Ice Shapes for an Engine Inlet,” AIAA-2010-7671, 2 nd AIAA Atmospheric and Space Environments Conference Toronto, Ontario August 2010
- Bidwell, C. “Icing Analysis of the NASA S3 Icing Research Aircraft Using LEWICE3D Version 2,” SAE Technical Paper 2007-01-3324 2007 10.4271/2007-01-3324