Wingtip design affects aerodynamic performance from drag reduction and stall performance. To properly optimize the design, it is necessary to explore which parameters affect the performance of the wingtip design. The test model was based on an existing Aksantara 115 UAV twin-boom design. This study investigates the effects of varying trailing edge curve parameters of the wingtip on the aerodynamic performance of the test model. A total of 4 variations were made from the baseline model, each model uses the general equation parameters of a conic section. These models are analyzed by using Computational Fluid Dynamics, employing the Reynolds Averaged Navier Stokes method with the $k-\varepsilon$ turbulence model. The angle of attack varied from -8 to 24 degrees with a flow velocity of 20 m/s. The results show that the wingtip device with circular curvature yields the highest aerodynamic efficiency.
CFD-Based Evaluation of Wingtip Device by Trailing Edge Curve Variation on Low Reynolds UAV
2023-10-26
1265454 byte
Conference paper
Electronic Resource
English
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