Design, Modelling and Analysis of Variable Span Wing
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Abstract
This paper elaborates the working principle of the aircraft wing with variable wing span particularly for unmanned aerial vehicles (UAVs). This concept is applied to create prototypes which could be used for wind tunnel testing and computational fluid dynamics (CFD) analysis. The aerodynamic characteristics for fixed span wing (FSW) and variable span wing (VSW) are analysed computationally. From the simulation, it is concluded that the VSW has provided at least 68% improvement in lift force at 5( angle of attack, as expected owing to the increased aerodynamic surface area with VSW.
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