TY - JOUR
T1 - Experimental Aerodynamic Simulation of Glaze Ice Accretion on a Swept Wing
AU - Broeren, Andy P.
AU - Potapczuk, Mark G.
AU - Lee, Sam
AU - Woodard, Brian S.
AU - Bragg, Michael B.
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 Chris Lum, Stephanie Camello, Kevin Ho and William Yoshida at the University of Washington. Selection of the artificial ice shapes and test conditions was supported by Emmanuel Radenac and Frédéric Moens at ONERA. Laurent Rossini, 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. Similar thanks are due also to Kevin Kelly, Aaron Kuenn, John Laffen and the staff at the WSU wind tunnel. 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:
© 2019 SAE International; NASA Glenn Research Center.
Copyright:
Copyright 2019 Elsevier B.V., All rights reserved.
PY - 2019/6/10
Y1 - 2019/6/10
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 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 8.9% and 13.3% scale semispan wing models based upon the Common Research Model airplane configuration. Various levels of geometric fidelity of an artificial ice shape representing a realistic glaze-ice accretion on a swept wing were investigated. The highest fidelity artificial ice shape reproduced all of the three-dimensional features associated with the glaze ice accretion. The lowest fidelity artificial ice shapes were simple, spanwise-varying horn ice geometries intended to represent the maximum ice thickness on the wing upper surface. The results presented in this paper show that changes in Reynolds and Mach number have only a small effect on the iced-wing aerodynamics relative to the clean-wing configuration. Furthermore, the addition of grit roughness to some lower-fidelity artificial ice shapes resulted in favorable lift and pitching moment comparisons to the wing with the highest fidelity artificial ice shape. For the wing with simple horn ice shapes, the dependence of maximum lift coefficient on horn height and angle are generally consistent with the trends observed for similar experiments conducted on iced airfoils in past research. In terms of usable lift however, the horn height did have a significant effect even for lower horn angles. This could be an important finding since usable lift may be more indicative of the impending iced-swept wing stall and need for additional pitch control than maximum lift coefficient.
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 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 8.9% and 13.3% scale semispan wing models based upon the Common Research Model airplane configuration. Various levels of geometric fidelity of an artificial ice shape representing a realistic glaze-ice accretion on a swept wing were investigated. The highest fidelity artificial ice shape reproduced all of the three-dimensional features associated with the glaze ice accretion. The lowest fidelity artificial ice shapes were simple, spanwise-varying horn ice geometries intended to represent the maximum ice thickness on the wing upper surface. The results presented in this paper show that changes in Reynolds and Mach number have only a small effect on the iced-wing aerodynamics relative to the clean-wing configuration. Furthermore, the addition of grit roughness to some lower-fidelity artificial ice shapes resulted in favorable lift and pitching moment comparisons to the wing with the highest fidelity artificial ice shape. For the wing with simple horn ice shapes, the dependence of maximum lift coefficient on horn height and angle are generally consistent with the trends observed for similar experiments conducted on iced airfoils in past research. In terms of usable lift however, the horn height did have a significant effect even for lower horn angles. This could be an important finding since usable lift may be more indicative of the impending iced-swept wing stall and need for additional pitch control than maximum lift coefficient.
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U2 - 10.4271/2019-01-1987
DO - 10.4271/2019-01-1987
M3 - Conference article
AN - SCOPUS:85067941652
VL - 2019-June
JO - SAE Technical Papers
JF - SAE Technical Papers
SN - 0148-7191
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 -