Experimental study of ice accretion effects on aerodynamic performance of an NACA 23012 airfoil

作     者：Sohrab Gholamhosein Pouryoussefi Masoud Mirzaei Mohammad-Mahdi Nazemi Mojtaba Fouladi Alireza Doostmahmoudi 

作者机构：Department of Aerospace EngineeringK.N.Toosi University of Technology 

出 版 物：《Chinese Journal of Aeronautics》 (中国航空学报（英文版）)

年 卷 期：2016年第29卷第3期

页      面：585-595页

核心收录：

学科分类：080103[工学-流体力学] 08[工学] 080104[工学-工程力学] 0801[工学-力学（可授工学、理学学位）] 

主　　题：Airfoil icing Aviation accidents:Horn ice NACA 23012 airfoilRunback ice Separation bobble Spanwise ridge ice 

摘      要：In this paper, the effects of icing on an NACA 23012 airfoil have been studied. Exper- iments were applied on the clean airfoil, runback ice, horn ice, and spanwise ridge ice at a Reynolds number of 0.6 x 10^6 over angles of attack from -8° to 20% and then results are compared. Gener- ally, it is found that ice accretion on the airfoil can contribute to formation of a flow separation bubble on the upper surface downstream from the leading edge. In addition, it is made clear that spanwise ridge ice provides the greatest negative effect on the aerodynamic performance of the airfoil. In this case, the stall angle drops about 10^6 and the maximum lift coefficient reduces about 50% which is hazardous for an airplane. While horn ice leads to a stall angle drop of about 4°and a maximum lift coefficient reduction to 21%, runback ice has the least effect on the flow pattern around the airfoil and the aerodynamic coefficients so as the stall angle decreases 2% and the maximum lift reduces about 8%.