FIELD: aircraft engineering.
SUBSTANCE: invention relates to aircraft engineering, particularly, to aircraft airfoil boundary layer control. Aircraft airfoil boundary layer control consists in making one or several channels with inlets in the form of air intakes arranged at aircraft airfoil leading edge in approach flow maximum pressure area. Outlets are configured as blowoff slits arranged at aircraft airfoil top surface trailing section to direct blowoff flow along the tangent or at some angle to airfoil. Said channels are configured so that total cross-section area of every inlet for every said channel is larger than that of outlets. Outlets of said channels make several rows of blowoff slits arranged serially at airfoil top surface.
EFFECT: power savings, higher aerodynamic properties.
6 cl, 5 dwg
