A series of cycloidal propellers were studied numerically under hovering status. The effects of the blade relative camber X and the location of the maximum camber Y of the blade on the aerodynamic performance of cycloidal propeller were studied respectively. The results indicated that compared with the cycloidal rotors with the blades of symmetrical airfoils

the aerodynamic performance of cycloidal propeller was improved greatly under the moderate camber and appropriate location of the maximum camber of the blade chord. When the relative camber X was 4%C (C was chord length) and the location of the maximum camber Y was at 40%C-50%C from the leading edge

the lift and power of the cycloidal propeller were relatively lower

the hovering efficiency was higher than other conditions

and the overall aerodynamic performance was better.