Method and apparatus for controlling the aerodynamics of an aircraft using an active flow control system is disclosed herein. In one example, the active flow control system includes an airframe and a plurality of fluidic oscillators. The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators is mounted about a curvature of the airframe. Each fluidic oscillator includes a body and an integral nozzle coupled to the body. The body has an inflow portion and a narrow nozzle inlet formed opposite the inflow portion. The integral nozzle is coupled to the body by the narrow nozzle inlet. The narrow nozzle inlet forms a single fluid flow path from the inflow portion to the narrow nozzle inlet.
Simplified fluidic oscillator for controlling aerodynamics of an aircraft
2020-07-21
Patent
Electronic Resource
English
IPC: | B64C AEROPLANES , Flugzeuge |
SIMPLIFIED FLUIDIC OSCILLATOR FOR CONTROLLING AERODYNAMICS OF AN AIRCRAFT
European Patent Office | 2017
|Simplified fluidic oscillator for controlling aerodynamics of an aircraft
European Patent Office | 2018
|A SIMPLIFIED FLUIDIC OSCILLATOR FOR CONTROLLING AERODYNAMICS OF AN AIRCRAFT
European Patent Office | 2019
|SIMPLIFIED FLUIDIC OSCILLATOR FOR CONTROLING AERODYNAMICS OF AN AIRCRAFT
European Patent Office | 2019
|