A method for analyzing the balance of shipboard helicopter landing is established by combining CFD model with flight dynamics model. On the premise of meeting calculation requirement of aerodynamic forces, Euler equations are used as governing equations for CFD model to improve calculative efficiency, and the momentum-source term is used to describe the effects of rotor and tail rotor on its flowfield. Aerodynamic forces calculated by the flight dynamics model are corrected by forces calculated by the CFD model. Furthermore, according to the Newton iteration method, trim parameters are obtained by solving the flight dynamics trim equations. By the proposed method, a validati1on example is given to show the effectiveness of the method. And then, the balance calculation of shipboard helicopter landing is performed.