FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engine production and aircraft engineering. Device to control airflow boundary layer comprises inner space, boundary layer suction channel and air blow channel arranged in compressor vanes and/or aircraft wings. Aforesaid channels communicate aforesaid space with ambient medium. Boundary layer suction channel represents either a continuous slot or tubular channels that pass along normal to blade and/or wing back surface from higher-pressure zone. Channel to blow air from aforesaid space into airflow lower-pressure zone passes at 5° to 15° to profile back along airflow. Nozzle flat variable rotary shapers can be arranged at air blow channel outlet. This invention covers also the method incorporating above described device.
EFFECT: stable airflow, increased angles of attack.
5 cl, 6 dwg
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