Experimental Aerodynamic Simulation of Glaze Ice Accretion on a Swept Wing 2019-01-1987
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 the 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 while both the thickness and location of the simply swept horn ice are important parameters to the resulting aerodynamics, the location is a much larger driver. These conclusions are consistent with the large volume of past research on iced-airfoils. However, some differences were also noted such as the effect of added surface roughness as described in this paper.
Andy P. Broeren, Mark G. Potapczuk, Sam Lee, Brian S. Woodard, Michael B. Bragg, Timothy G. Smith
NASA Glenn Research Center, NASA John Glenn Research Center, Vantage Partners Limited, Univ of Illinois at Urbana-Champaign, Univ of Washington, FAA Technical Center
International Conference on Icing of Aircraft, Engines, and Structures