Influence of Realistic Aircraft Conditions on Accretion of Supercooled Large Droplet 2023-01-1408
The present paper deals with the accretion of supercooled large droplets (SLD) at high velocity on wall. A visualization technique of the accretion of ice is used to measure and characterize the thickness of ice during the accretion phenomenon. Influences of air velocity, air temperature, drop size, impact angle and altitude were studied. The experiments are conducted in the ONERA icing wind tunnel, which allows to reach regimes close to realistic conditions for aircrafts (i.e. high velocity: → 190 m/s and altitude: → 11 500 m).
Citation: Dejean, B., Alary, T., Duchayne, Q., and Berthoumieu, P., "Influence of Realistic Aircraft Conditions on Accretion of Supercooled Large Droplet," SAE Technical Paper 2023-01-1408, 2023, https://doi.org/10.4271/2023-01-1408. Download Citation
Author(s):
Baptiste Dejean, Thomas Alary, Quentin Duchayne, Pierre Berthoumieu
Affiliated:
ONERA
Pages: 9
Event:
International Conference on Icing of Aircraft, Engines, and Structures
ISSN:
0148-7191
e-ISSN:
2688-3627
Related Topics:
Icing and ice detection
Wind tunnel tests
Aircraft
Imaging and visualization
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