Aiming at the noise of helicopter scissors tail-rotor ,an advanced numerical method is established by combining computational fluid dynamics (CFD) model with Farassat 1A (F1A) formula .In this method ,Navier-tokes (N-S) equations are used as goving equations ,and the flow field is solved at quasi-steady and unsteady states in hover and forward fight ,respectively ,based on two different types of embedded grid systems .A simple and effective solution approach is provided for the generation difficulty of donor cells caused by the close gap among scissors tail-rotor blades .Using the CFD calculation results as input ,the thickness noise ,loading noise and total noise of tail-rotor are calculated by F1A formula .By the method ,numerical examples on rotor flowfield and noise are performed and the results are compared with available data .Then ,aerodynamic and acoustic characteristics of scissors tail-rotor are emphatically calculated in both hover and forward flight .Furthermore ,the research on the effects of blade-tip shape parameters on scissors tail-rotor noise is carried out .Also ,the scissors tail-rotor is com-pared with the conventional tail-rotor ,and the results show that in hover ,the noise of a scissors tail-rotor is not al-ways the smaller one .