Experimental aerodynamic characteristics of NACA 0012 airfoils with simulated glaze and rime ice

Ice formation constitutes one of the major challenges to aviation safety, since several accidents have had their origin in this kind of phenomenon. The comprehension of ice accretion on unprotected airfoils, engine intakes, etc. is fundamental from the point of view of both aircraft design and certification requirements since large changes in aerodynamic behaviour and performance take place. The present paper describes tests conducted in a conventional wind tunnel on NACA 0012 airfoils with simulated rime and glaze ice, using laser Doppler velocimetry to measure the flow around the modified airfoils and also the velocity profiles along the viscous wake in order to obtain the drag coefficient. Distortions of the flow field lead to changes in the airfoil aerodynamic characteristics.