It is clear that the improvement of aircraft aerodynamic performances is currently and will continue to be a significant area of research for the aeronautical industry. The current study is focused on theenhancement of aerodynamic airfoil performances by using a multi-DBD plasma actuator mounted around the model leading-edge. Experiments have been conducted at the University of Orleans, in the 2 m x 2 m test section of a large wind tunnel in which a NACA0012 airfoil was mounted in a 2D flow configuration. Tests have been carried out in a velocity range of 10 - 40 m.s-1, resulting in Reynolds numbers based on the chord length of 200,000 ≤ Re ≤ 800,000. The actuator consisted of copper electrodes flush mounted with an asymmetric disposition on both sides of a dielectric panel constituted by four layers of Kapton® tape, and with saw-like grounded electrodes and floating inter-electrodes. This multi-DBD plasma actuator ensures a thinwall jet produced tangentially to the dielectric surface and continuously accelerated along the successive discharges. Aerodynamic load measurements and Particle Image Velocimetry have been performed to characterize the benefits of the control. Results show potentialities of such actuator to delay stall configuration and to enhance lift in a full post-stall separated flow.
Authors
- Annie Leroy,
- Pierre Audier,
- Janusz Podlinski,
- Artur Berendt link open in new tab ,
- Dunpin Hong,
- Jerzy Mizeraczyk
Additional information
- Category
- Aktywność konferencyjna
- Type
- publikacja w wydawnictwie zbiorowym recenzowanym (także w materiałach konferencyjnych)
- Language
- angielski
- Publication year
- 2012
