Abstract: This paper introduces the development and application of an advanced time-accurate multidisciplinary technique for the prediction of unsteady aerodynamics and flight dynamics of maneuvering projectiles. The virtual flight simulation of a basic finner projectile has been investigated through coupling solving procedure of unsteady Navier-Stokes equations, rigid-body six degree-of-freedom motion equations and control law. The flow solver uses a finite-volume method based on structure grid with dual time stepping. Additionally, a feedback controller is required for the control surfaces to attain the commanded deflections, and the overset Chimera method is used to simulate relative motions. The predictions show that the gains for the controller must be correctly selected to obtain the proper response. Simulation results show that the virtual flight simulation platform developed here is capable of solving the complicated unsteady flows with moving boundary, has a strong promotion to engineering application.