Abstract

A rotating icing scaling law used for parameter selection for tests in an icing wind tunnel is established using the basic physical process of icing. The method of selecting parameters for a scale model of rotating components is also discussed. A dimensionless quantity, called the rotation number, is derived from the water film momentum equation in the rotating coordinate system. This parameter must be matched between the reference and the scale model. Water collection properties and ice accretion are numerical calculated through the similarity law established in this study to evaluate the effectiveness of the rotating icing similarity law. Results show that when the rotating speed of the full size cone is 1000 or 3000 r/min, nearly identical droplets collection features and ice shape can be obtained for the half scale model. Thus, the established rotating icing similarity law is effective and can be used as the theoretical guidance for parameter selection for ice wind tunnel tests.

Keywords:

Ice shape , rotating icing scaling law , rotation number , water collection property,

References

1. Anderson, D.N. 1994. Rime-, Mixed- and Glaze-Iced Evaluations of Three Scaling Laws. Proceedings of the 32th Aerospace Sciences Meeting and Exhibit. Reno, NV. AIAA-94-0718.
   CrossRef    
2. Anderson, D.N., 1996. Further Evaluation of Traditional Icing Scaling Methods. National Aeronautics and Space Administration, Washington, DC.
   CrossRef    
3. Anderson, D.N. and G.A. Ruff, 1999. Evaluation of methods to select scale velocities in icing scaling tests. Proceedings of the 37th AIAA Aerospace Sciences Meeting and Exhibit. Reno, NV, AIAA 99-0244.
   CrossRef    
4. Bilanin, A.J., 1991. Proposed modifications to ice accretion/icing scaling theory. J. Aircraft, 28(6): 353-359.
   CrossRef    
5. Irving, L. and B. Katherine, 1946. A mathematical investigation of water droplet trajectories. Army Air Force Technical Report, No. 5418.
   
6. Kind, R.J., M.G. Potapczuk, A. Feo, C. Golia and A.D. Shah, 1998. Experimental and computational simulation of in-flight icing phenomena. Prog. Aerosp. Sci.., 34(5): 275-345.
   CrossRef    
7. Messinger, B.L., 1953. Equilibrium temperature of an unheated icing surface as a function of airspeed. J. Aeronaut. Sci., 20(1): 29-42.
   CrossRef    
8. Paraschivoiu, I., P. Tran and M.T. Brahimi, 1994. Prediction of ice accretion with viscous effects on aircraft wings. J. Aircraft, 31(4): 855-861.
   CrossRef    
9. Pope, A., 1947. Wind Tunnel Testing. 2nd Edn., John Wiley and Sons, Inc., New York.
   
10. Qiu, X.G. and F.H. Han, 1985. Deicing Aircraft System. 1st Edn., The Aviation Industry Publication, Beijing.
    PMCid:PMC1192966    
11. Qiuyue, Z., 2010. Computational analysis of water droplet impingerment property for the inlet struct and the cone. M.S. Thesis, Shanghai Jiao Tong Univ., Shanghai.
    
12. Ruff, G.A. 1985. Verification and application of the icing scaling equations. Final Report, AIAA-86- 26640.
    
13. Ruff, G.A., 1986. Analysis and verification of the icing scaling equations. M.S. Thesis, University of Tennessee, Knoxville.
    
14. Yi, X., 2007. Numerical computation of aircraft icing and study on icing test scaling law. M.S. Thesis, China Aerodynamics Research and Development Center, Sichuan.
    

Competing interests

The authors have no competing interests.

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