CBL - Campus del Baix Llobregat

Projecte llegit

Títol: A numerical study of Flow control on wings using Vortex Generators

Estudiants que han llegit aquest projecte:

Director/a: ALTMEYER, SEBASTIÁN ANDREAS

Departament: FIS

Títol: A numerical study of Flow control on wings using Vortex Generators

Data inici oferta: 16-02-2024     Data finalització oferta: 16-10-2024


Estudis d'assignació del projecte:
    GR ENG SIS TELECOMUN
    GR ENG SIST AEROESP
    GR ENG TELEMÀTICA
Tipus: Individual
 
Lloc de realització: EETAC
 
Paraules clau:
Pasive Flow control, Vortex generators, Aerodynamic efficiency and optimization, Drag reduction, Grid Error Refinement
 
Descripció del contingut i pla d'activitats:
This project deals with the investigation of aerodynamic and performance parameters over an eliptical wing. This mainly includes the Active flow control techniques such as multi-sweeping jets which are used in airfoils/wings that will help us to analyze the lift and drag parameters. The jet configurations are studied and modified to obtain reduction of viscous drag, improvement in pressure distribution and interference effects over and below the airfoil and maximize lift coefficient.

Pre- and Post processing stage would include the generation of a complete wing design with built-in sweeping jets using software as Gmesh or Solidworks. It requires parametric inputs like altering the position of jets in order to calculate the induced drag and thus decrease the drag effects. The use of this open source also results in advanced visualization capabilities of airfoil and parallel further analysis and simulation would be carried out using AnsysFluent. Aside the design will be implemented in SolidWorks and a 3D model will be printed in tested at the EETAC wind tunnel. Correlation between experimental and numerical results will be analyzed.

The required software tools for the project are SolidWorks, Gmesh, Matlab, Ansys, Fluent to carry out implementation and simulations.
 
Overview (resum en anglès):
Stalled wings present a very dangerous situation for the users of aicrafts, even if in the last decades great improvements in safety have been done, the investigation for new ways of delaying wing stall keep on. In this work a numerical approach has been done with the objective of simulating a wing of profile NACA 4415 with and without vortex generators with the objective of comprehending more in detail the phenomena of boundary layer separation and doing a validation process of the results comparing them with experimental data from literature. Also a verification process has been carried on stuyding the discretization error in the mesh employed for the simulations and to find and adequate size for the fluid domain size.
The turbulance model chosen was Spalart Allmaras because it is known to give good results for aerospace application and run for several angles of atack.

According to the simulations results, the numerical models employed seem to resemble closely the experimental values up to 10º of angle of attack, and then the error starts to increase showing a premature boundary layer detachment and a smaller lift generation for the wing configuration with vortex generators in comparison with the bare wing configuration. Also an adequate fluid domain size has been chosen and the discretization error found was rather small.
For the 2D simulation it was found that it captures better the lift coeffcient values at angles of attack near stall, but it was not the case with the drag coeffcient for which low values were obtained.

For further improvements, if more computational resources are available the turbulance model LES could be a better option as it is known to capture the boundary layer detachment in a better way, also the known as micro vortex generator are known to give good results.

© CBLTIC Campus del Baix Llobregat - UPC