This content is not included in your SAE MOBILUS subscription, or you are not logged in.
3D Computational Methodology for Bleed Air Ice Protection System Parametric Analysis
ISSN: 0148-7191, e-ISSN: 2688-3627
Published June 15, 2015 by SAE International in United States
Annotation ability available
A 3D computer model named AIPAC (Aircraft Ice Protection Analysis Code) suitable for thermal ice protection system parametric studies has been developed. It was derived from HASPAC, which is a 2D anti-icing model developed at Wichita State University in 2010. AIPAC is based on the finite volumes method and, similarly to HASPAC, combines a commercial Navier-Stokes flow solver with a Messinger model based thermodynamic analysis that applies internal and external flow heat transfer coefficients, pressure distribution, wall shear stress and water catch to compute wing leading edge skin temperatures, thin water flow distribution, and the location, extent and rate of icing. In addition, AIPAC was built using a transient formulation for the airfoil wall and with the capability of extruding a 3D surface grid into a volumetric grid so that a layer of ice can be added to the computational domain. Currently, the grid extrusion capability is used in AIPAC for the so called one-shot ice shape computation. The icing tunnel data used in the validation of the proposed computer model were obtained at the NASA Icing Research Tunnel using a range of in-flight icing conditions and bleed air system mass flows and hot air temperatures. Predicted leading edge skin temperatures and runback ice location are compared to the experimental data. Correlation between experiment and analysis was good for most of the test cases used to assess the performance of the simulation model. AIPAC's transient formulation will also allow future development of a thermodynamic model for the simulation of electro-thermal de-icing systems.
CitationDomingos, R. and Silva, D., "3D Computational Methodology for Bleed Air Ice Protection System Parametric Analysis," SAE Technical Paper 2015-01-2109, 2015, https://doi.org/10.4271/2015-01-2109.
- Domingos , R. H. , Papadakis , M. , and Zamora , A.O. Computational Methodology for Bleed Air Ice Protection System Parametric Analysis AIAA paper 2010-7834 2010 10.2514/6.2010-7834
- Papadakis , M. , Wong , S. , Yeong , H. , Wong , S. et al. Experimental Investigation of a Bleed Air Ice Protection System SAE Technical Paper 2007-01-3313 2007 10.4271/2007-01-3313
- Papadakis , M. , Wong , S.-H. , Yeong , H.W. , Wong , S.C. , and Vu , G.T. Icing Tunnel Experiments with a Hot Air Anti-Icing System AIAA Paper 2008-0444 Jan. 2008
- Papadakis , M. , Wong , S.-H. , Yeong , H.W. , Wong , S.C. , and Vu , G.T. Icing Tests of a Wing Model with a Hot-Air Ice Protection System AIAA Paper 2010-7833 Aug. 2010
- Papadakis , M. , Zamora Rodriguez , A. , and Domingos , R. Experimental and Computer Model Results for a Bleed Air Ice Protection System SAE Technical Paper 2011-38-0034 2011 10.4271/2011-38-0034
- Al-Khalil , K.M. Numerical Simulation of an Aircraft Anti-Icing System Incorporating a Rivulet Model for the Runback Water Ph.D. Thesis University of Toledo Toledo, OH 1991
- Wright , W.B. User Manual for the NASA Glenn Ice Accretion Code LEWICE Version 2.2.2 NASA CR-211793 Aug. 2002
- Papadakis , M. , Wong , S.-H. , Yeong , H.W. , Wong , S.C. , and Vu , G.T. Icing Tunnel Experiments with a Hot Air Anti-Icing System AIAA paper 2008-444 Jan. 2008
- Fortin , G. , Laforte , J. , and Beisswenger , A. Prediction of Ice Shapes on NACA0012 2D Airfoil SAE Technical Paper 2003-01-2154 2003 10.4271/2003-01-2154
- Messinger , B. L. Equilibrium Temperature of an Unheated Icing Surface as a Function of Air Speed Journal of the Aeronautical Sciences Jan. 1953 29 42