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EVALUATION OF AERODYNAMIC PERFORMANCE OF AIRFOIL USING THE E-MPS METHOD AFTER ICING
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ABSTRACT
Accumulation of ice on aircraft can lead to severe problems in terms of safety; therefore, development of a method by which these issues can be simulated is required. In this study, the effects of several icing conditions such as inflow velocity, liquid water content, and the angle of attack on the ice accretion on an airfoil are numerically investigated using a particle-based method. The computational target is a NACA0012 airfoil with a chord length of 0.53 m, and droplets with a diameter of 1.0 mm are used in all cases. The icing simulations are carried out with different inflow velocities, liquid water contents, and angle of attack ranging from 50-140 m/s, 0.2-1.6 g/m3, and -8-20 degrees, respectively, with standard values of 50 m/s, 1.2 g/m3, and 4 degrees. The explicit moving particle simulation method, which is based on the Lagrangian approach, is employed to obtain complex ice shapes such as feathers. Moreover, aerodynamic performance before and after icing is also compared at different attack angles, using the ice shapes obtained with the moving particle method. It was confirmed that the feather shape, which is difficult to produce with the present lattice method, was reproduced using the particle-based method. The results indicated that icing decreases the stalling angle, and this decrease deteriorates aerodynamic performance by a maximum of 56.2%.
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