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Additional Comparison of Iced Aerodynamic Measurements on a Swept Wing from Two Wind Tunnels
ISSN: 2641-9645, e-ISSN: 2641-9645
Published June 10, 2019 by SAE International in United States
Citation: Lee, S., Broeren, A., Woodard, B., Lum, C. et al., "Additional Comparison of Iced Aerodynamic Measurements on a Swept Wing from Two Wind Tunnels," SAE Int. J. Adv. & Curr. Prac. in Mobility 2(1):175-191, 2020, https://doi.org/10.4271/2019-01-1986.
Artificial ice shapes of various geometric fidelity were tested on a wing model based on the Common Research Model. Low Reynolds number tests were conducted at Wichita State University’s Walter H. Beech Memorial Wind Tunnel utilizing an 8.9% scale model, and high Reynolds number tests were conducted at ONERA’s F1 wind tunnel utilizing a 13.3% scale model. Several identical geometrically-scaled ice shapes were tested at both facilities, and the results were compared at overlapping Reynolds and Mach numbers. This was to ensure that the results and trends observed at low Reynolds number could be applied and continued to high, near-flight Reynolds number. The data from Wichita State University and ONERA F1 agreed well at matched Reynolds and Mach numbers. The lift and pitching moment curves agreed very well for most configurations. This confirmed results from previous tests with other ice shapes that indicated the data from the low Reynolds number tests could be used to understand iced-swept-wing aerodynamics at high Reynolds number. This allows ice aerodynamics testing to be performed at low Reynolds number facilities with much lower operating costs and generate results that are applicable to flight Reynolds number.
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