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Independent Effects of Reynolds Number and Mach Number on the Aerodynamics of an Iced Swept WingAerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional (3D) icing simulation capabilities. An understanding of ice-shape geometric fidelity and Reynolds and Mach number effects on the iced-wing aerodynamics is needed to guide the development and validation of ice-accretion simulation tools. To this end, wind tunnel testing was carried out for a 13.3-percent-scale semispan wing based upon the Common Research Model airplane configuration. The wind tunnel testing was conducted at the Office National d’Etudes et de Recherches Aérospatiales (ONERA) F1 pressurized wind tunnel with Reynolds numbers of 1.6 x 10(exp 6) to 11.9 x 10(exp 6 ) and Mach numbers of 0.09 to 0.34. Five different configurations were investigated using fully 3D, high-fidelity artificial ice shapes that maintain nearly all of the 3D ice-accretion features documented in prior icing wind tunnel tests. These large, leading-edge ice shapes were nominally based upon airplane holding in icing conditions scenarios. For three of these configurations, lower fidelity simulations were also built and tested. The results presented in this paper show that while Reynolds and Mach number effects are important for quantifying the clean-wing performance, there is very little to no effect for an iced wing with 3D, high-fidelity artificial ice shapes or 3D smooth ice shapes with grit roughness. These conclusions are consistent with the large volume of past research on iced airfoils. However, some differences were also noted for the associated stalling angle of the iced swept wing and for various lower fidelity versions of the leading-edge ice accretion. More research is planned to further investigate the key features of ice-accretion geometry that must be simulated in lower fidelity versions in order to capture the essential aerodynamics.






Document ID
20190027696
Acquisition Source
Glenn Research Center
Document Type
Technical Memorandum (TM)
Authors
Broeren, Andy P. (NASA Glenn Research Center Cleveland, OH, United States)
Lee, Sam (Vantage Partners, LLC Brook Park, OH, United States)
Woodard, Brian S. (Illinois Univ. at Urbana-Champaign Urbana, IL, United States)
Lum, Christopher W. (Washington Univ. Seattle, WA, United States)
Smith, Timothy G. (Federal Aviation Administration (FAA) Atlantic City, NJ, United States)
Date Acquired
July 24, 2019
Publication Date
July 1, 2019
Subject Category
Aeronautics (General)
Report/Patent Number
NASA/TM-2019-220012
GRC-E-DAA-TN61957
AIAA–2018–3492
E-19620
Funding Number(s)
CONTRACT_GRANT: SAA3-1402
CONTRACT_GRANT: NNC12BA01B
WBS: 081876.02.03.50.08.05
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Aircraft icing
Scale models

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