No abstract

In the present study, the optimum wing and its aerodynamic performance investigation of an Active aeroelastic wing (AAW) structure for an unmanned aerial vehicle that operates at low subsonic speed is presented. AAW technology is a new design for UAV wing structures which ultimately increases its efficiency. The focus is mainly to design a seamless flexible wing structure. The shape changes made from root to tip wing twist enhance the aerodynamic performance of the UAV. Because of the shape change, the weight carrying capacity of the UAV can be increased. In the fluid domain, Numerical Analysis has been done for both the wing. The simulation was performed with maximum velocity of 60 m/s and Reynolds number of 81300 based on incompressible Navier-Stokes equations using 1-equation spalart allmaras turbulent model in CFD and based on the Lifting line theory and vortex lattice approach in XFLR5. Here investigation is about to compare the aeroelastic wing by changing its angle of twist with the normal wing by deflecting its flap. The final goal was to compare the AAW and normal wing computationally by varying their speed, lift-based, and drag-based best result of both the wing has arrived. Drag breakdown analysis on an AAW UAV wing platform is done utilising classical approach, XFLR5, and CFD aerodynamic coefficients estimation methods.