The reliability and applicability of two overset mesh methods were verified. Then numerical analysis of the unsteady vortex flow and induced separation characteristics of cycloidal propeller in the two-/three-dimensional cases was carried out

laying the foundation for studying the distribution of spanwise aerodynamics with azimuth and the induced velocity distribution of the global flow field

meanwhile the wake capture accuracy and vorticity dissipation characteristics were also analyzed. Results showed that

under the influence of three-dimensional effects such as tangential velocity and spanwise induced velocity of cycloidal propeller

the difference of transient aerodynamic extremum between the two calculation results reached 44%. The generation

shedding and reattachment of three-dimensional dynamic stall vortices were obviously weaker than two-dimensional airfoil

yielding a great impact on the unsteady aerodynamic characteristics of cycloidal propeller.