Additional Comparison of Iced Aerodynamic Measurements on a Swept Wing from Two Wind Tunnels 2019-01-1986
Identical 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 Beech Memorial Wind Tunnel, and high Reynolds number tests were conducted at ONERA’s F1 wind tunnel. The ice shapes tested in this report were in addition to those reported in a previous paper. The aerodynamic performance data from the two facilities were compared at matched Reynolds number to ensure that the results and trends observed at low Reynolds number could be applied and continued to high Reynolds number. The data from Wichita State University and F1 agreed well at matched Reynolds numbers, which was consistent to the results published in the previous report. The lift and pitching moment curves agreed very well for most configurations. This confirmed the results of the previous report which indicated that data from the low Reynolds number tests could be used to understand iced-swept-wing aerodynamics at high Reynolds number.
Sam Lee, Andy Broeren, Brian Woodard, Christopher Lum, Timothy Smith
Vantage Partners Limited, NASA Glenn Research Center, Univ of Illinois at Urbana-Champaign, University of Washington, FAA Technical Center
International Conference on Icing of Aircraft, Engines, and Structures