TY - GEN
T1 - Effect of simulated scalloped ice on the aerodynamics of a swept-wing at low-reynolds number
AU - Sandhu, Navdeep
AU - Soltani, Mohamad Reza
AU - Bragg, Michael B.
AU - Lum, Christopher W.
AU - Woodard, Brian S.
AU - Broeren, Andy P.
AU - Lee, Sam
N1 - Funding Information:
The authors would like to thank Dr. Mark Potapczuk from NASA for his contributions to the test preparation and execution. The team would also like to thank the many members at the University of Washington Aircraft Icing and Aerodynamics Research Group including Stephanie Camello, Gustavo Fujiwara, and Kevin Ho for their contributions to test preparation, execution, and analysis. John Laffen, Kevin Kelly, Aaron Kuen, and Ryan Benyshek at the Walter H. Beech Memorial Wind Tunnel at Wichita State University were immensely helpful with test preparation, execution, and data acquisition. The authors would also like to thank Dr. James Riley and Timothy Smith from the FAA for their contributions to the project. This work was funded by FAA grant 15-G-009.
Publisher Copyright:
© 2018, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2018
Y1 - 2018
N2 - This paper studied the aerodynamic effects of a single scalloped ice accretion and a low fidelity ice-shape simulation. These data were compared to the aerodynamics of a clean 8.9% scale CRM65 semispan wing model at a Reynolds number of 1.6 x 106. The clean wing experienced an aggressive, tip-first stall and showed a small, strong leading-edge vortex at lower angles-of-attack while the iced cases showed larger, seemingly weaker leading-edge vortices at similar angles. The size of these vortices is larger for the low-fidelity ice shape. The stall pattern for the iced cases was also tip-first, but more gradual than the clean wing. The high-fidelity ice shape produced streamwise flow features over the upper surface of the wing due, in part, to flow moving through gaps that exist in the ice shape geometry that disrupted the formation of the leading-edge vortices, changing the aerodynamics of the wing. These gaps do not exist in the low-fidelity shape. The low-fidelity scallop ice shape was non-conservative in its aerodynamic penalties compared to the full high-fidelity case.
AB - This paper studied the aerodynamic effects of a single scalloped ice accretion and a low fidelity ice-shape simulation. These data were compared to the aerodynamics of a clean 8.9% scale CRM65 semispan wing model at a Reynolds number of 1.6 x 106. The clean wing experienced an aggressive, tip-first stall and showed a small, strong leading-edge vortex at lower angles-of-attack while the iced cases showed larger, seemingly weaker leading-edge vortices at similar angles. The size of these vortices is larger for the low-fidelity ice shape. The stall pattern for the iced cases was also tip-first, but more gradual than the clean wing. The high-fidelity ice shape produced streamwise flow features over the upper surface of the wing due, in part, to flow moving through gaps that exist in the ice shape geometry that disrupted the formation of the leading-edge vortices, changing the aerodynamics of the wing. These gaps do not exist in the low-fidelity shape. The low-fidelity scallop ice shape was non-conservative in its aerodynamic penalties compared to the full high-fidelity case.
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U2 - 10.2514/6.2018-3495
DO - 10.2514/6.2018-3495
M3 - Conference contribution
AN - SCOPUS:85051634668
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 -