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Etude expérimentale du décollement sur profils d'aile : analyse et contrôle

Abstract : The separation of a boundary layer is generally an undesirable aerodynamic phenomenon over a pitched airfoil due to its adverse effects on the performances of the wing.
Many authors have shown that it is possible to suppress or, at least, to delay separation by introducing control devices named « actuators » over the airfoil. Fluidic actuators have been tested on two experimental configurations: a NACA 0015 airfoil where a trailing-edge separation is occurring and an ONERA D, a symmetric airfoil characterized by leading-edge separation. The actuators, which are installed on the upper side of the wing, are composed either by a series of discrete injectors or a thin slot, the blowing being either steady or unsteady.
We have studied the influence of different parameters (actuator geometry, excitation frequency and intensity...). We have discovered a significant modification of the flow structures under the effects of control which favour the reattachment process and lead to a lift increase and a considerable decrease in drag.
This study is dedicated to the control authority of fluidic actuators in reattaching a separated shear layer. It is the first step towards the implementation of reactive control system. Future works involve the study of the physics of the dynamic process of attachment and separation.
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Submitted on : Thursday, July 31, 2008 - 7:55:28 PM
Last modification on : Wednesday, October 20, 2021 - 3:22:05 AM
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Sébastien A. C. Bourgois. Etude expérimentale du décollement sur profils d'aile : analyse et contrôle. Sciences de l'ingénieur [physics]. Université de Poitiers, 2006. Français. ⟨tel-00308715⟩

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