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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 factor. The Navier-Strokes (NS) 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.