FIELD: aviation.
SUBSTANCE: device for increase of lifting properties of an aircraft is designed as a flat ridge with the rounded leading edge, leading edge sweep angle near fuselage is 40°÷50°. By means of smooth rounding the leading edge passes into a lateral edge forming with the fuselage surface an angle 5° maximum. Trailing edge is straight and forms with the lateral edge a sharp angle 60°÷75°. The device length amounts 10÷15% of the chord of the near-board section wing of the aircraft. The device height amounts 20÷25% of its length. The central part of the device is of constant thickness. The device is installed on the fuselage as a vortex generator.
EFFECT: increase of wing lift coefficient.
4 dwg
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