Evaluation of Small Scale Icing Tunnel Test Results

Document Number: 2007-01-3328

Date Published: September 2007

Author(s):
Sarah Barley - Airbus

Abstract:
A test has been performed using a scaled aircraft wing section in an icing tunnel facility. The model had an electro-thermal ice protection system installed. The tests performed considered both anti-icing and de-icing modes of operation. The results have been assessed using numerical codes and the effect of model scaling has been considered. The non-scaled skin thickness of the model was found to modify the predicted behavior of a full-scale installation, predominantly due to lateral conduction effects. The extent of this has been assessed and recommendations are made as to the performance that may be expected at full-scale.

File Size: 295K
Product Status: In Stock

See other papers presented at 2007 SAE Aircraft and Engine Icing International Conference, September 2007, Seville, SPAIN, Session: In-flight Ice Detection Systems

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