Abstract
Winglet is a tool used to improve the efficiency of aircraft and UAV performance by preventing fluid flow jump from lower surface to upper surface at wingtip. The addition of this winglet resulted in improved lift and reduction of drag force from the aircraft wing or UAV. From Whitcomb's research, it was found that the use of winglet on a full size airplane can increase fuel efficiency by 7%. The research led to the idea of conducting research on fluid flow characteristics on the UAV wing with the Eppler 562 airfoil combined with the whitcomb winglet. This numerical study was conducted using the Computational Fluid Dynamics (CFD) method based on the advantages of using this simulation that can review the fluid flow in macroscopic way. This study is provide accurate fluid flow visualization results and can improve the performance of the wings when compared with wings without winglet (plain wing). Wing with the Eppler 562 airfoil combined with the whitcomb winglet results reduction in rotating motion that makes velocity components as opposed to lift.
Highlights
The limited wing length results in a three-dimensional flow occurring at the tip due to the pressure difference on the upper surface and the lower side of the wing
This research study of the fluid flow characteristics of the plane wing with the Eppler 562 airfoil type combined with the whitcomb winglet type winglet, where the angle of attack on the airfoil became a variable that could be varied. This numerical study was conducted using the Computational Fluid Dynamics (CFD) method based on the advantages of using this simulation that can review the fluid flow in macroscopic way
At the angle of α = 12o, there is a difference in the flow phenomenon across the airfoil midspan
Summary
The limited wing length results in a three-dimensional flow occurring at the tip due to the pressure difference on the upper surface and the lower side of the wing. This flow resulted in the emergence of a vortex or so-called tip vortex. The tip vortex resulted in reduce of effective area and increased drag coefficient on the aircraft. Weirman (2010) conducted research in the form of numerical simulations and experiments on the performance of Whitcomb winglet and blended winglet on UAV. Weirman's research yielded the conclusions of improving lift coefficient (CL) on whitcomb winglet and blended winglet, and predicting increased aircraft resistance on winglets using winglets
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