Abstract: Based on dynamic hybrid mesh and the coupling solver of N-S equations, rigid body dynamic equations and flight controlling law, a CFD-based numerical virtual flight technique is presented. A wing/store separation case is examined to validate the coupling solver. Finally, preliminary applications of this numerical method are carried out, including the attack angle controlling process, the acceleration load controlling process of a missile with and without Mach number varying. These cases demonstrate the robustness and accuracy of the present solver.