Yilmaz, Remzi CanAkbiyik, Hurrem2026-02-272026-02-2720251343-88751875-897510.1007/s12650-025-01071-8http://dx.doi.org/10.1007/s12650-025-01071-8https://hdl.handle.net/20.500.14669/4364This paper deals with the effects of three distinct ice accumulations on the aerodynamic performance of the NACA 2415 airfoil. The experiments are carried out for the base airfoil as well as glaze (GIA), rime (RIA), and horn ice (HIA) accumulated airfoils at Re = 1.2 x 105. For this study, force and velocity measurements are taken. Additionally, the oil and smoke-wire flow visualization techniques were performed. The selected range of angle of attack for force measurements is defined as -7 degrees to 23 degrees. In addition, considering the results of force measurements, seven distinct angle of attack values including 0 degrees, 4 degrees, 8 degrees, 13 degrees, 14 degrees, 17 degrees and 20 degrees are chosen for velocity measurements and flow visualization experiments. Experimental results showed that CLmax of ice accreted airfoils are decreased as expected. 20%, 23% and 88% of decrease in maximum lift coefficient are observed in the GIA, RIA and HIA models, respectively. Increases in drag coefficients at alpha = 0 degrees for the GIA, RIA and HIA airfoils are observed to be around 14%, 4% and 307%, respectively. A sudden increase in lift coefficient of the GIA airfoil is observed at post-stall. Moreover, a double-peak behavior is noted for the GIA and RIA airfoil, and also for the base airfoil in velocity measurements.eninfo:eu-repo/semantics/closedAccessIce accretionHorn iceGlaze iceRime iceAerodynamic performanceArticle770474928WOS:001498142600001