Analysis on the aerodynamic efficiency of modified blended wingtip

Abstract

As aircrafts fly, a lot of lift needed to ensure maximum thrust can be generated. However, as lift increase, induced drag also will increase. One of the problems due to drag usually happen at the wingtip. Vortices will be formed at the wingtip and create pressure above the wing. Therefore, reduce lift. In order to overcome this problem, various wingtip shapes are being applied at the wingtip. The purpose of this analysis is to analyse the aerodynamic efficiency of modified blended wingtip. This analysis consists of blended wingtip and modification of the wingtip itself based on different speed and angle of attack. From this analysis, the lift and drag ratio from the coefficient of lift and drag obtained for the blended wingtip and all the design will be compared and therefore, analyse the efficiency of the applied modification. The analysis involving wing of NACA 4415 with four different types of wingtip; the original blended wingtip, modification 1 with 15° plane added, modification 2 with 30° plane added and modification 3 with 45° plane added, four different speed and so do four different angle of attack (AOA). All of these designs will be analysed by using Computational Fluid Dynamic (CFD) software. From the analysis, the efficiency can be determined by comparing the lift and drag ratio. The result from the analysis has been proved that modification of blended wingtip with 45° plane added has the highest lift and drag coefficient that is 2.16 X 10 -1 at highest angle of attack at 30 m/s compared to blended wingtip and design modification of blended wingtip with 15° and 30° added plane.