Optimisation of a Nacelle Electro-Thermal Ice Protection System for Icing Wind Tunnel Testing
Author:
Affiliation:
1. 1 Department of Aerospace Science and technology, Politecnico di Milano , Via La Masa, 34 , 20156 Milano , Italy
2. 2 Leonardo S.p.a. , Piazza Monte Grappa, 4 , 00195 rome , Italy
Abstract
Publisher
Walter de Gruyter GmbH
Link
https://www.sciendo.com/pdf/10.2478/tar-2023-0004
Reference22 articles.
1. Cole, J. and Sand, W. “Statistical Study of Aircraft Icing Accidents”. Proceedings 29th Aerospace Sciences Meeting. p. 558. 1991. Reno, Nevada (USA).
2. Jones, S.M., Reveley, M.S., Evans, J.K., and Barrientos, F.A. “Subsonic Aircraft Safety Icing Study.” NASA/tM-2008-215107. (No. L-19435). 2008.
3. Lou, D. and Hammond, D.W. “Heat and Mass transfer for Ice Particle Ingestion Inside Aero-engine.” ASME. Journal of Turbomachinery, July 2011; 133(3): 031021. DOI 10.1115/1.4002419.
4. Al-Khalil, K., Horvath, C., Miller, D., Wright, W., Al-Khalil, K., Horvath, C., Miller, D., and Wright, W. “Validation of Nasa thermal Ice Protection Computer Codes. III-the Validation of Antice.” Proceedings 35th Aerospace Sciences Meeting and Exhibit. p. 51, 1997. reno, Nevada (USA).
5. Beaugendre, H., Morency, F., and Habashi, W.G. “FENSAP-ICE’s three-Dimensional In-Flight Ice Accretion Module: ICe3D.” Journal of Aircraft Vol. 40, No. 2 (2003): pp. 239–247.
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