CBL - Campus del Baix Llobregat

Projecte llegit

Títol: Drag reduction on NACA arifoil at ultralow Reynolds numbers via sweeping jet active flow control


Estudiants que han llegit aquest projecte:


Director/a: MELLIBOVSKY ELSTEIN, FERNANDO PABLO

Departament: FIS

Títol: Drag reduction on NACA arifoil at ultralow Reynolds numbers via sweeping jet active flow control

Data inici oferta: 10-02-2021     Data finalització oferta: 10-10-2021



Estudis d'assignació del projecte:
    GR ENG SIST AEROESP
Tipus: Individual
 
Lloc de realització: EETAC
 
Paraules clau:
Airfoil, Aerodynamics, Active Flow Control, Sweeping Jet, NACA0012, Quasi-3D, 2.5D
 
Descripció del contingut i pla d'activitats:
The aim of the project is to assess the performances of a sweeping jet active flow control mechanism acting on a stalled NACA airfoil at ultralow Reynolds numbers. The work plan will include

1) Literature review on stalled airfoil performances and Active Flow Control methods.
2) Computation of the 2D baseline case.
3) Assessment of the most unstable spanwise modes.
4) Implementation of the 3D sweeping jet
5) Analysis of the results
 
Overview (resum en anglès):
Aeronautics industry experienced its greatest expansion in terms of technological development in the Second World War and Cold War periods. Since then, progress has been made over the avionics, the aerodynamics, the airspace organization, management and infrastructure with the aim of optimizing them. This project wants to follow this line and to perfect the aerodynamic properties of an airfoil, to make it optimal not only in cruise conditions (the flight stage where the airfoil is going to be the majority of its useful life), but in each flight stage such as the take-off, landing, approach and ascension phases.

So the project¿s investigation field will be the active control of the airfoil¿s boundary layer at high angles of attack and low Reynolds numbers, so as to emulate those critical flight stages that were mentioned before, using flux injection dispositives or sweeping jets placed at the wing¿s extrados. This aims to increase the aerodynamic efficiency of a three-dimensional wing by energizing the boundary layer in order to delay its separation while avoiding the use of movable parts. A sweeping jet consists of a fluidic actuator which emits a time and space oscillating jet without having any mechanical or electromagnetic part.

The Reynolds numbers used are unrealistically low for actual aeronautical applications due to the interest in the physical mechanisms of actuation control, which are only feasible at very low Reynolds regimes. This study aims to expand the chord-wise positioning optimization studies, to the optimization in the span-wise direction of the positioning and self separation between actuators, taking advantage of the homogeneity in that direction, by using single modal and multi modal Fourier expansions of variable wave number in order to reduce computational complexity and time.


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