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).


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    Title :

    A SIMPLIFIED FLUIDIC OSCILLATOR FOR CONTROLLING AERODYNAMICS OF AN AIRCRAFT


    Additional title:

    VEREINFACHTER FLUIDOSZILLATOR ZUR STEUERUNG DER AERODYNAMIK EINES FLUGZEUGES
    OSCILLATEUR FLUIDIQUE SIMPLIFIÉ POUR CONTRÔLER L'AÉRODYNAMIQUE D'UN AÉRONEF


    Contributors:

    Publication date :

    2019-11-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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