FIELD: transportation, aviation.
SUBSTANCE: device contains suction system openings in aerodynamic surface and plate on aerodynamic surface. The device is equipped with static-pressure sensors or thermal anemometers located along flow streamline of boundary layer and intended for determination the flow mode in boundary layer. The device is shifted along wing chord from flow streamline to wing trailing edge to exclude additional flow distortions along flow streamline with possibility to eliminate limitation of suction rate when Red ≤100.
EFFECT: excluding the turbulent effect of plate on boundary layer when suction is disabled or preset mode has failed.
3 dwg
