Numerical Simulation of Aerodynamic Performance of Wing with Split Winglets

Abstract

Winglet is an additional surface in a form of vertical or horizontal extension of the wing. The shape of winglet changed during the development period and depending on the type of aircraft on which they were installed. Due to its benefits and influence on aircraft performance during the flight, the standard end of wing has been replaced by new configurations. The geometry of the winglet depends on the required performance and is unique in each application. The angle (or edge) of the winglet, its inner or outer angle, and its size and shape are critical parameters for wing performance. Winglets can increase the range and reduce fuel consumption. With split winglets, the expected reduction in fuel consumption is up to 1.5 %. This type of additional surface on the wing increases the effective aspect ratio of the wing without increasing the structural load. This paper investigates the performance of the wing with and without the split winglets and constant airfoil b737c-il at angles of attack (0, 10o and 20o), at the speed of 0.8 Mach. Wing model was designed in CATIA P3 V5 software package. The aerodynamic drag and lift coefficients CD and CL, as well as their change with the angle of attack, were obtained by finite volume method (FVM) in ANSYS Fluent software.