Carleton University

Published purpose

Modern aircrafts have deicing systems normally using 1) special materials, 2) weeping anti-ice fluid, 3) heated bleeding air, 4) electrical heaters, 5) pneumatic boots, or 6) vibrating electro-mechanical surfaces placed at the leading edge of the wings and horizontal stabilizers. Pilots must decide to activate the system if icing is observed and adjust the approach by increasing the landing velocities by 37 km/h (20 knots). Several accidents have occurred due to aircraft icing accretion. Manufacturers require enhanced test facilities and more effective 3D computational tools to design and certify aircraft against more stringent icing requirements. The current investigation aims at the assessment and development of 3D numerical techniques to model aircraft icing accretion with de-icing systems. Flows around the test platform of various geometries will be simulated with a turbulence model including impinging super-cooled water droplets, which will be compared with in situ ice accretion measurements.