Blade shape is a main factor influencing the hover performance of coaxial rigid rotors, therefore, it is of great significance to investigate how blade shapes affect hover performance of this configuration. In order to improve the accuracy of analyzing the parameter effect, firstly, a CFD method based on movingembedded grid technique and the compressible Reynoldsaveraged NavierStokes equations is established to solve the flowfield of coaxial rigid rotors. Then, calculations and analyses of hover aerodynamic performance are conducted, and the blade lift and torque distributions along the azimuth and blade spanwise are obtained by using this method. Finally, parameter analyses of blade shapes on hover performance are conducted, consisting of swept angle, swept position and nonlinear chord distribution. The Figure of Merit (FM) and pressure distribution of coaxial rigid rotors with different parameters are obtained. The results show that swept tips could make negative pressure region move outward, delay flow separations and improve FM. Considerable taper tips and larger chord distributions in the middle of blade could effectively unload blade tips, improve airload distributions and increase hover performance.