TY - JOUR
T1 - Additional Comparison of Iced Aerodynamic Measurements on a Swept Wing from Two Wind Tunnels
AU - Lee, Sam
AU - Broeren, Andy
AU - Woodard, Brian
AU - Lum, Christopher
AU - Smith, Timothy
N1 - Funding Information:
The authors would like to thank the many collaborators without whom this work would not have been possible. Mark Potapczuk at NASA, Michael Bragg and Kevin Ho at the University of Washington, and Frédéric Moens and Emmanuel Radenac at ONERA provided key contributions to this work. The authors would also like to acknowledge the staff at the Walter H. Beech Memorial Wind Tunnel at Wichita State University and ONERA F1 wind tunnel for their outstanding support. This work was supported through international and interagency agreements between NASA, the FAA, and ONERA. 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. The Universities of Washington and Illinois were funded for this program by FAA grant 15-G-009 with support from Dr. James T. Riley.
Publisher Copyright:
© 2019 SAE International; NASA Glen Research Center.
PY - 2019/6/10
Y1 - 2019/6/10
N2 - 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.
AB - 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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U2 - 10.4271/2019-01-1986
DO - 10.4271/2019-01-1986
M3 - Conference article
AN - SCOPUS:85067941261
SN - 0148-7191
VL - 2019-June
JO - SAE Technical Papers
JF - SAE Technical Papers
IS - June
T2 - 2019 SAE International Conference on Icing of Aircraft, Engines, and Structures, ICE 2019
Y2 - 17 June 2019 through 21 June 2019
ER -