Numerical analysis and optimization of a winglet sweep angle and winglet tip chord for improvement of aircraft flight performance

Abstract

In the present research, an investigation of the influence of winglet sweep angle and winglet tip chord of the aircraft wing on the aerodynamics properties and how to make it better has been carried out, assuming Cant angle 60, winglet height = 3.5 m, Toe angle = -5, and Twist angle = +5. Sweep angles (-25, -15, 0, +15, +25, +35, and +45) and winglet tip chord (0.25, 0.375, and 0.5 m) have been tested. AOA (0, 3, 6, and 9) have been presented. The aerodynamics parameters were measured in terms of calculating the L/D for deciding which wing formation possesses a maximum value of lift and a minimum drag. The whole models (eighty-four models) of a wing were plotted in three dimensions employing the wing dimensions e SOLIDWORKS software. A civilian transport airplane "Boeing 737" wing dimensions were used. A CFD simulation using ANSYS FLUENT for all models of wings was conducted. The results manifested that the sweep angle and winglet tip chord of the winglet by changing their shape can enhance the aerodynamic performance for different angles of attack. The ultimate L/D value was determined with a sweep angle -15, winglet tip chord 0.375 m, and AOA 3.

Keywords

• cfd
• angle of attack
• winglet
• lift and drag coefficient
• sweep angle