Aerodynamic Analysis by CFD Simulation VS Wind-Tunnel Test to reduce Drag of UAV Aircraft

This work proposes an effective numerical models based on the Computational Fluid Dynamics (CFD) approach VS Wind-tunnel Measurements to obtain the optimum Drag reduction, by studying flow dynamics around a UAV plane with different shapes of (nose cones & boat tails). The experimental work of the test vehicle and grid system is constructed by ANSYS-16.2 FLUENT which is the CFD solver & employed in the present work. In this study, numerical iterations are completed, then after aerodynamic data and detailed complicated flow dynamics are visualized. In the present work, model of the UAV has been designed & developed in solid works-18 and generated the wind tunnel and applied the boundary conditions in ANSYS workbench 16.2 platform then after testing and simulation has been performed for the evaluation of drag coefficient for the UAV. In another case, the aerodynamics of the most suitable three designs of (nose cones & boat tails) is introduced to be manufactured for the Wind-tunnel Measurements evaluation in full scale Wind-Tunnel for the optimum drag coefficient for this UAV by comparison between both data of (CFD) and Wind-tunnel Measurements. Erasing the stagnation faces is totally reduces drag in head-on wind and bring about the significant improvements in the aerodynamic efficiency of the UAV planes with Streamlined shapes, it can be obtained. Hence, the drag force can be reduced by using add on parts on vehicles and fuel economy, battery economy and stability of a planes can be improved [1].