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Aerodynamic measurements on a finite wing with simulated iceThe effect of a simulated glaze ice accretion on the aerodynamic performance of a three-dimensional straight and swept wing is studied experimentally. A semispan wing of effective aspect ratio five was mounted from the sidewall of the UIUC subsonic wind tunnel. The model uses an NACA 0012 airfoil section on a rectangular planform with interchangeable tip and root sections to allow for 0- and 30-deg sweep. A sidewall suction system is used to minimize the tunnel boundary-layer interaction with the model. A three-component sidewall balance has been designed, built and used to measure lift, drag and pitching moment on the clean and iced model. Fluorescent oil flow visualization has been performed on the iced model and reveals extensive spanwise flow in the separation bubble aft of the upper surface horn. These results are compared to computational results for the surface pressures, span loads and surface oil flow.
Document ID
19910069116
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Bragg, M. B.
(Illinois Univ. Urbana, IL, United States)
Khodadoust, A.
(Illinois Univ. Urbana, IL, United States)
Soltani, R.
(Illinois Univ. Urbana, IL, United States)
Wells, S.
(Illinois Univ. Urbana, IL, United States)
Kerho, M.
(Illinois, University Urbana, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-3217
Accession Number
91A53739
Distribution Limits
Public
Copyright
Other

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