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Contrôle expérimental de l'écoulement tourbillonnaire sur une aile delta

Abstract : This study concerns the fluidic control of the leading-edge vortices over a 60° sweep angle delta wing with a rounded leading-edge. Firstly, we report experimental measurements on the flow field to characterize the effects of the geometry. Laser Doppler Velocimetry allows us to analyse the linear stability of the vortices. The results of the nominal test conditions establish a basis for studying the influence of the flow control. Secondly, we apply a pulsed or steady blowing at the leading-edge through four thin slots whose frequency and momentum flux are variable. Pulsed blowing is not effective to affect the global characteristics of the flow field. However, the steady control results in the upstream shift of the breakdown location and increases the maximum normal force and pitching moment. An asymmetric control produces a significant rolling moment around certain incidence angles.
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Contributor : Florent Renac <>
Submitted on : Thursday, December 7, 2006 - 9:58:14 PM
Last modification on : Wednesday, December 9, 2020 - 3:09:15 PM
Long-term archiving on: : Wednesday, April 7, 2010 - 12:07:32 AM


  • HAL Id : tel-00119173, version 1


Florent Renac. Contrôle expérimental de l'écoulement tourbillonnaire sur une aile delta. Dynamique des Fluides [physics.flu-dyn]. Université Pierre et Marie Curie - Paris VI, 2004. Français. ⟨tel-00119173⟩



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