Recently there has been significant research in the field of Unmanned Aerial Vehicles (UAV). For efficient deployment and operation of these vehicles, it is imperative that one understands the physical system. This in turn involves one to design efficient control algorithms for implementation in these platforms. Thus we need algorithms and methods that identify the physical system parameters, that in turn can be used to design robust model based control systems. This thesis employs CAE software such as SolidWorks, GAMBIT and FLUENT to calculate the aerodynamic coefficients and moment of inertia. The aerodynamic coefficients are analyzed to understand the sensitivity of the aerodynamic forces and moments due to change in angle of attack, side slip angle and control surface detection. A detailed procedure on how to configure the various parameters required for solving the fluid flow around an R/C airplane is demonstrated. Moment of inertia and center of mass are calculated using SolidWorks for empty and full fuel tank of the airplane model and compared against experimental results based on the pendulum method.
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