摘要：Icing will occur when helicopters pass through clouds containing supercooled droplets. The ice accreted on rotor blade affects the safety of helicopter. A numerical simulation method of helicopter rotor icing in forward flight is presented, and the icing characteristics of rotor are studied. The flow field is calculated based on the overlapping grids, and the Eulerian model is applied in the droplet trajectory calculation. The unsteady method is used to calculate rotor flow field and droplet trajectory. The icing model considering the effect of centrifugal force is adopted to simulate the ice shapes of rotor in forward flight. The average ice growth rate is compared with the ice growth rate at each azimuth angle, and the effects of blade pitch and forward flight speed on the droplet impingement and icing characteristics are summarized. Finally, the influence of time step on the calculation results is analyzed. The calculation results show that the droplet impingement characteristics and icing characteristics change continuously in forward flight. The ice growth rate and droplet collection efficiency are larger on the advancing blade and smaller on the retreating blade.
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