HYBRID AIRFOIL DESIGN FOR FULL-SCALE ICE ACCRETION TEST  

作　　者：郭涛 朱程香 朱春玲 

机构地区：[1]College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics [2]Key Laboratory of Fundamental Science for National Defense Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2013年第2期139-144,共6页南京航空航天大学学报（英文版）

基　　金：Supported by the National Natural Science Foundation of China(10972106)

摘　　要：A hybrid airfoil inverse design method according to the target pressure distribution and the impingement efficiency is presented.The method is 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 are calculated to obtain pressure distribution and impingement efficiency firstly.The Navier-Strokes(N-S)solver is used in flow field calculation to improve calculation precision.The droplet impingement and ice accretion on the airfoil are 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 full-scale leading edges and redesigned aft-section.The hybrid airfoil can be tested under 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.Moreover,the ice shapes formed on the full-scale and hybrid airfoils are compared at various attack angles.The results demonstrate that ice shapes between hybrid and full-scale airfoils match well and the developed method is effective.A hybrid airfoil inverse design method according to the target pressure distribution and the impingement efficiency is presented. The method is 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 are calculated to obtain pressure distribution and impingement efficiency firstly. The Navier-Strokes（N-S） solver is used in flow field calculation to improve calculation precision. The droplet impingement and ice accretion on the airfoil are per- formed 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 full-scale leading edges and redesigned aft-section. The hybrid airfoil can be tested under 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. Moreover, the ice shapes formed on the full-scale and hybrid airfoils are compared at various attack angles. The results demonstrate that ice shapes between hybrid and full-scale airfoils match well and the developed method is effective.

关 键 词：hybrid airfoil pressure distribution droplet impingement ice accretion 

分 类 号：V244.1[航空宇航科学与技术—飞行器设计]