This paper considers computational fluid dynamics (CFD) analysis and experimental test strength verification of the UAV wing made of composite materials. The CFD calculation and static strength testing results of specific UAV wing are illustrated. Specific attention was given to the definition of aerodynamics loads acting on UAV wing and experimental tests of UAV wing. For a precise definition of aerodynamic loading of UAV in this work the commercial CFD software was used. The work aims to carry out one-way fluid–solid interaction (FSI) for UAV structural design, in which aerodynamics loads obtained from CFD analysis can be applied on the vehicle structure for steady-state static FE analysis. To determine precise aerodynamic loads of UAV in this research, the complete “tail-aft on booms” shaped configuration UAV is modelled and analyzed using CFD numerical simulation.