Abstract: An aerodynamic device (1, 11), such as for an aircraft, including a frame (2), a skin (6) forming an aerodynamic surface and connected to the frame (2) and a motile portion (4) adapted to be displaced between a first position in which the aerodynamic surface exhibits a first shape, and a second position different from the first position, wherein the mobile portion includes a disturbing structure (3), and in the second position of the motile portion (4), and the aerodynamic surface exhibits a second shape in which the disturbing structure (3) induces a protrusion (14) on the aerodynamic surface.

Abstract: A fluidic oscillator device, in particular for a or in a flow control system for an aircraft or spacecraft, has a first and a second fluidic actuator, wherein each of the actuators has an inlet for supplying pressure and a first and a second outlet, from which an actuator flow can be discharged. The device further has a fluidic control for controlling an oscillating discharge of the actuator flow from the first and second outlet of the actuators, wherein the control has a connection portion which is arranged between the first actuator and the second actuator.