Numerical analysis for evaluating the effect of some common factors on rotor aerodynamics was conducted with an in-house CFD solver

in which a second-order upwind finite-volume and dual time-stepping scheme were used for Navier-Stokes equations discretization under an embedded grid system; and the numerical process was accelerated by OMP parallel technique.The involved problems mainly include the effect of background grid points scale on tip-vortex capture in hover

shock wave in forward flight and blade force

and the differences between the aerodynamics results obtained with/without 1D momentum far field boundary condition.The calculated rotor lift and torque discrepancy in hover are approximately 6% and 2.6% with different background grid points

and the drag and torque discrepancy in forward flight are 2.58% and 3.28% separately. The lift results show about 3%-5% difference with and without 1D momentum far field boundary condition correction.The fluctuation range of rotor aerodynamics with above-mentioned parameters was given by calculation

providing useful reference in rotor aerodynamics simulation.