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A Flow Visualization Study of the Leading Edge Separation Bubble on A NACA 0012 Airfoil With Simulated Glaze IceAs a part of an ongoing research in aircraft icing, the leading edge separation bubble on a NACA 0012 model with a 5 min simulated glaze ice was investigated. The flow visualization methods using oil, tuft, splitter plate, smoke, and liquid crystals were employed to get reattachment line data for the leading edge separation bubble on both surfaces of the airfoil. On the upper surface, the separation bubble was found to grow larger with increasing angles of attack and reduce in size with decreasing angle of attack. On the lower surface, the bubble was found to grow larger with increasing negative angles of attack and reduce in size with increasing angles of attack. The separated flow fails to reattach beyond 6° for the upper surface and -5° for the loser surface. Their results of this study compared well with those of other experiments and computational results.
Document ID
19880005584
Acquisition Source
Glenn Research Center
Document Type
Contractor Report (CR)
Authors
Abdollah Khodadoust
(The Ohio State University Columbus, Ohio, United States)
Date Acquired
September 5, 2013
Publication Date
January 1, 1988
Publication Information
Publisher: National Aeronautics and Space Administration
Subject Category
Fluid Mechanics and Thermodynamics
Report/Patent Number
NASA-CR-180846
NAG3-28
Accession Number
88N14966
Funding Number(s)
CONTRACT_GRANT: NAG3-28
WORK_UNIT: 505-68-11
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.
Keywords
Aircraft icing
Iced airfoil flowfield measurements
Computer code validation data
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