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Títol: Flow study around an aircraft’s wing with (and without) wing tip device for several models

Director/a: CASTAN PONZ, JOSÉ ANTONIO

Departament: DEGD

Títol: Flow study around an aircraft’s wing with (and without) wing tip device for several models

Data inici oferta: 30-01-2019 Data finalització oferta: 30-09-2019

Estudis d'assignació del projecte:

GR ENG SIST AEROESP

Tipus: Individual

Lloc de realització: EETAC

Paraules clau:
efficient winglet for A320

Descripció del contingut i pla d'activitats:
study the behavior of the flow in presence of winglets

Overview (resum en anglès):
The aim of this project is to study the wing tip vortices, its preventions implemented until now and introduce a new design. The aerodynamic performance analyzation of the Airbus A320’s wing with and without wing tip devices was carried out. Winglets are being used to have a bigger aspect ratio of the wing because it will help to reduce the induced drag caused by vortices. This unwanted swirling effect is created by the pressure imbalance at the wing tip, where higher pressure of the lower surface meets the lower pressure of the upper surface. A solution to this inconvenience, is the design of the winglets which is able to reduce the induced drag. The airfoils design plays an important role in the aerodynamic efficiency of a wing. Therefore, several NACA airfoils were selected in order to compare their behaviour and the models chosen are: NACA0009, NACA0012, NACA2411, NACA4412 and NACA6412. These airfoils gone through flow simulation in ANSYS FLUENT. After analysing them at several angles of attack, CL/CD ratios were compared to nominate the best airfoil. The results of CFD simulations confirms that NACA6412 is the best aerodynamically performed airfoil to be used for A320’s wing construction. The wing was modelled in Solidworks without and with wing tip devices as Sharklet, Wingtip Fence, Feathered Wingtip (new concept) and Raked Wingtip. In order to obtain the Lift force and Drag force the use of Solidworks Flow Simulation was needed. These different wing configurations were studied again in different angles of attack to examine their aerodynamic performance. The best winglet model increases the ratio between CL and CD decreasing the wing tip vortices which will be pointed out at the end of the project.