Hybrid airfoil design for full-scale ice accretion test
This paper presents a hybrid airfoil design method combined the genetic algorithm with inverse design method according to the target pressure distribution and impingement efficiency. The method was developed to design hybrid airfoils that simulate the droplet impingement and ice accretion of full-scale airfoil. Flow field and droplet impingement around the full-scale airfoil were calculated to obtain pressure distribution and impingement efficiency firstly. A N-S solver was used in flow field calculation to improve calculation precision. The droplet impingement and ice accretion on the airfoil were performed by FENSAP-ICE. Once the target chord or original airfoil is given, the hybrid airfoil geometries can be computed. The designed hybrid airfoil consists of a full-scale leading edges and redesigned aft-section. The hybrid airfoil can be tested at full-scale conditions to produce full-scale ice accretion in the exiting icing tunnels which are too small to perform ice accretion testing of full-scale airfoils. The paper presents a comparison between the ice shapes that formed on the full-scale and hybrid airfoil at various angles of attack. The results demonstrate ice shapes between hybrid and full-scale airfoil match well and the developed method is effectively.
hybrid airfoil pressure distribution droplet impingement ice accretion
Tao Guo Chunling Zhu
The First Aircraft Institute, Aviation Industry Corporation, PO Box 72-311, Xian 710089, China Coll College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016
国际会议
2011年亚太航空航天技术学术会议(APISAT 2011)
澳大利亚
英文
1-7
2011-02-28（万方平台首次上网日期，不代表论文的发表时间）