This report represents an initial effort directed to CFD-based analysis of maneuvering air vehicles, including aircraft and missiles, targeting ultimately to serve robust dynamic analysis and optimal control problems of single vehicle as well as groups of vehicles interacting in combat. The background of the research work comes from the need for Multi-Disciplinary Optimization (MDO) of modern combat air vehicles with improved manoeuverability. One engineering challenge is how to optimally utilize a given aircraft, another is to accurately predict the manoeuvring performance of a concept during the design stage. In reference to the current state of the art in CFD-based simulations of manoeuvring air vehicles and, making steps forwards, the establishment of a multidisciplinary platform is targeted for simulating and modelling air-vehicle maneuvers. To achieve the purpose, it is recognized that a primary effort must be initially dedicated to a comprehensive understanding of the aerodynamics of the manoeuvring air-vehicle and to an effective implementation of related CFD techniques, including the governing equations of the flow motion and relevant boundary conditions. The governing equations of the flow around a maneuvering air vehicle are revisited, by assuming a rigid-body motion as a moving reference frame (MRF) undergoing system translation and rotation. The equation system is cast in either tensorial or vectorial form, both leading to consistent source terms in relation to the fictitious forces in a non-inertial frame of reference. It is recognized that in the moving reference frame the solutions to the relative velocity and the total energy defined in terms of the relative velocity may be degraded in the presence of very large source terms accompanying with a large computational domain. In the actual CFD implementation, the momentum equations and the equation for the total energy have thus been re-formulated in order to alleviate the numerical effect of source terms, by taking into account angular and translation velocity and accelerations in a general framework. For constant system rotation, the equation system lies in the same context as given in the current M-Edge solver. To facilitate the CFD implementation based on the MRF method, a simple test case has been set up for effective validation in simulating the flow around the NACA0015 airfoil that is subjected to oscillating pitching motion and rotation. Moreover, for validation of the CFD-based method in computing dynamic derivatives, as references, two existing panel methods have been modified and extended at this stage to compute dynamic damping derivatives. The results based on the mesh deformation method and the panel method will be further deployed in validation the CFD implementation of the MRF method in M-Edge. The present report is expected to be a relevant reference in the follow-up CFD implementation, validation and verification in analysis of maneuvering air vehicles.