FIELD: aviation.
SUBSTANCE: invention relates to aircraft flow control systems at subsonic and nearsonic flight speeds. The pulse plasma heat actuator of the ejector type comprises an underwater channel with a check valve, a discharge chamber with built-in needle electrodes, an ejector nozzle, a mixing chamber, a rarefaction cavity with a slit connecting the rarefaction cavity with the surface of the wing, and an output diffuser. The actuator allows to create a high-speed pulsating jet of gas flowing from the nozzle without overheating of the working area in one area of the flow and simultaneously carry out the boundary layer exhaust into the other one.
EFFECT: expanded possibility of controlling the aircraft wing flow.
2 dwg
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