Experimental Aerodynamic Simulation of Glaze Ice Accretion on a Swept Wing

Andy P. Broeren, Mark G. Potapczuk, Sam Lee, Brian S. Woodard, Michael B. Bragg, Timothy G. Smith

Research output: Contribution to journalConference article

Abstract

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.

Original languageEnglish (US)
JournalSAE Technical Papers
Volume2019-June
Issue numberJune
DOIs
StatePublished - Jun 10 2019
Event2019 SAE International Conference on Icing of Aircraft, Engines, and Structures, ICE 2019 - Minneapolis, United States
Duration: Jun 17 2019Jun 21 2019

ASJC Scopus subject areas

  • Automotive Engineering
  • Safety, Risk, Reliability and Quality
  • Pollution
  • Industrial and Manufacturing Engineering

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    Broeren, A. P., Potapczuk, M. G., Lee, S., Woodard, B. S., Bragg, M. B., & Smith, T. G. (2019). Experimental Aerodynamic Simulation of Glaze Ice Accretion on a Swept Wing. SAE Technical Papers, 2019-June(June). https://doi.org/10.4271/2019-01-1987