TY - GEN
T1 - Independent effects of reynolds and mach numbers on the aerodynamics of an iced swept wing
AU - Broeren, Andy P.
AU - Lee, Sam
AU - Woodard, Brian S.
AU - Lum, Christopher W.
AU - Smith, Timothy G.
N1 - Funding Information:
The authors wish to acknowledge the contributions of several key collaborators. Specifically, this work would not have been possible without the unique and outstanding contributions of Mark Potapczuk at NASA Glenn Research Center; Frédéric Moens and Emmanuel Radenac at ONERA; and Mike Bragg, Stephanie Camello and Kevin Ho at the University of Washington. William Yoshida, an undergraduate student at the University of Illinois also developed and implemented the algorithm to create the contour plots of surface pressure from the individual pressure-tap data. Laureline Torz Dupuis, Grégoire d'Ozouville, Grégoire Charpentier, Denis Guérin, and the staff at the ONERA F1 wind tunnel provided exemplary support for the experimental portion of this work. The FAA and ONERA supported this research through interagency and international agreements, respectively. The NASA-supported portion of this research was originally funded under the Atmospheric Environment Safety Technologies Project of the Aviation Safety Program with continued support under the Advanced Air Transport Technology and Aeronautics Evaluation and Test Capabilities Projects of the Advanced Air Vehicles Program. These individuals, organizations and projects are gratefully acknowledged.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - Aerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional 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%-scale semispan wing based upon the Common Research Model airplane configuration. The wind-tunnel testing was conducted at the ONERA F1 pressurized wind tunnel with Reynolds numbers of 1.6×106 to 11.9×106 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.
AB - Aerodynamic assessment of icing effects on swept wings is an important component of a larger effort to improve three-dimensional 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%-scale semispan wing based upon the Common Research Model airplane configuration. The wind-tunnel testing was conducted at the ONERA F1 pressurized wind tunnel with Reynolds numbers of 1.6×106 to 11.9×106 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.
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U2 - 10.2514/6.2018-3492
DO - 10.2514/6.2018-3492
M3 - Conference contribution
AN - SCOPUS:85051622898
SN - 9781624105586
T3 - 2018 Atmospheric and Space Environments Conference
BT - 2018 Atmospheric and Space Environments Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 10th AIAA Atmospheric and Space Environments Conference, 2018
Y2 - 25 June 2018 through 29 June 2018
ER -