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University of Illinois at Urbana-Champaign
Effects of Supercooled Large -Droplet Icing on Airfoil Aerodynamics
Abstract
dc:descriptionThe effects of simulated ice shape on the NLF 0414 were quite different from the NACA 23012m. There was little variation of lift when the simulated ice-shape location was varied from 2% to 20% chord. The large losses in lift occurred when the ice shape was located downstream of 30% chord, and the separation bubble formed over the adverse pressure gradient of the clean airfoil, which started at 75% chord. The effect of the ice shape on the NLF 0414 was not as severe as on the NACA 23012m because the lift was much more aft loaded.
Degree
thesis:*- Name thesis:degree_name
- Ph.D.
- Level thesis:degree_level
- Dissertation
- Discipline thesis:degree_discipline
- Aerospace Engineering
- Grantor
- University of Illinois at Urbana-Champaign
- Year dc:date
- 2015
Author and committee
dc:creator, dc:contributor.*- Author dc:creator
-
- Lee, Sam
- Contributors dc:contributor
-
- Bragg, Michael B.
Subjects
dc:subject × 1Rights
- Language dc:language
- eng
Identifiers
dc:identifier.*- Identifier
- (MiAaPQ)AAI3017141
- OAI identifier oai:identifier
- oai:www.ideals.illinois.edu:2142/85067