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 (200). The airframe includes an inlet configured for flight speeds ranging from subsonic to hypersonic. The plurality of fluidic oscillators (200) is mounted about a curvature of the airframe. Each fluidic oscillator (200) includes a body (202) and an integral nozzle (204) coupled to the body (202). The body (202) has an inflow portion (206) and a narrow nozzle inlet (208) formed opposite the inflow portion (206). The integral nozzle (204) is coupled to the body (202) by the narrow nozzle inlet (208). The narrow nozzle inlet (208) forms a single fluid flow path (218) from the inflow portion (206) to the narrow nozzle inlet (208).
A SIMPLIFIED FLUIDIC OSCILLATOR FOR CONTROLLING AERODYNAMICS OF AN AIRCRAFT
VEREINFACHTER FLUIDOSZILLATOR ZUR STEUERUNG DER AERODYNAMIK EINES FLUGZEUGES
OSCILLATEUR FLUIDIQUE SIMPLIFIÉ POUR CONTRÔLER L'AÉRODYNAMIQUE D'UN AÉRONEF
2019-11-06
Patent
Elektronische Ressource
Englisch
IPC: | B64C AEROPLANES , Flugzeuge |
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