In the framework of the PLASMAERO European project, experiments were conducted to investigate the authority of surface DBD plasma actuators to alter a fully separated flow around an airfoil in order to improve its aerodynamic performances in its natural stall regime. In this paper, unsteady excitation control is more specifically investigated. The key control parameter studied here is the burst frequency which periodically imposes switching on and off the actuator. Results show that it is possible to perform a modification of the massively separated flow by unsteady excitation near the leading-edge. However, depending on the forcing frequency and the post-stall regime, two different flow modification mechanisms can be observed leading to either the reduction of the flow separation or the occurrence of a mean large lifting vortex next to the suction side. In both cases, a large lift increase is obtained.
Authors
- Annie Leroy,
- Pierre Audier,
- Dunpin Hong,
- J. Podliński,
- Artur Berendt link open in new tab ,
- Jerzy Mizeraczyk
Additional information
- Category
- Publikacja w czasopiśmie
- Type
- artykuły w czasopismach
- Language
- angielski
- Publication year
- 2013
