Aircraft wing

FIELD: aircraft engineering.

SUBSTANCE: aircraft wing comprises triangular body secured to fuselage and furnished with vertical oncoming airflow splitters arranged at body edge each having leading and trailing sections. Leading section is arranged ahead of body edge parallel about vertical plane extending along fuselage. One of trailing edges is attached to top airfoil and bent aside from fuselage. Another trailing section is secured to bottom airfoil and bent towards fuselage. Angle of the bend of splitter trailing section secured to top airfoil makes 5-15 degrees. Angle of the bend of splitter trailing section secured to bottom airfoil makes 5-15 degrees.

EFFECT: increased lift.

3 cl, 5 dwg

 

The invention relates to the field of modeling high-speed manned and unmanned aerial vehicles for civil applications with wing triangular form.

Known wing of the aircraft, containing attached to the fuselage triangular body, equipped with a vertically mounted on its edge dividers oncoming air flow [1].

The objective of the invention is to increase the lifting force of the wing of the aircraft.

The technical solution of the task is achieved by the fact that the wing of the aircraft, containing attached to the fuselage triangular body, equipped with a vertically mounted on its edge dividers oncoming air stream, each divider has a head and two tail section, and the head portion is located in front of the edge of the body parallel to the vertical plane passing along the fuselage, one of the tail sections attached to the upper aerodynamic surface of the body with the limb away from the fuselage, and the other a tail section attached to the lower aerodynamic surface of the body contour in the side of the fuselage. The angle of the limb of the tail section of the divider attached to the upper aerodynamic surface is 5-15°. The angle of the limb of the tail section of the divider con is captive to the lower aerodynamic surface, is 5-15°.

In Fig.1 shows an aircraft with wing triangular, General view; Fig.2 depicts a fragment of the body of the wing is installed on the edge of the divider incident flow of Fig.3 shows the air flow divider, front view; Fig.4 - view of Fig.3, side view; Fig.5 is a view of Fig.3, above.

Wing 1 aircraft (Fig.1) containing attached laterally to the fuselage 2 triangular rigid body 3, with the upper 4 and lower 5 aerodynamic surfaces. The body may be solid, porous, have a frame. Aerodynamic surfaces can be traditional (N. E. Zhukovsky) or that, for example, a thin flat profile. On the edge 6 of the body from oncoming air flow installed vertically dividers 7. The dividers can be in the form of an ellipse (Fig.2), oval, rectangle, triangle (not shown). Each divider has a head 8 and the two separated by a slot 9, the tail section, respectively, 10 and 11. The size of the slot corresponds to the thickness of the edges of the body of the wing. Head portion of the divider is located in front of the edge of the body parallel to the vertical plane Q passing along the fuselage. The tail section attached to the upper aerodynamic surface, made with the limb away from the fuselage and the tail section attached kniznej aerodynamic surface, made with the limb to the side of the fuselage (Fig.3 and 4). The angle α of the limb of the tail section of the divider attached to the upper aerodynamic surface is 5-15° relative to the line o-x (Fig.5). The angle β of the limb of the tail section of the divider attached to the lower aerodynamic surface is 5-15°.

From alloys of aluminum, titanium and other materials make model high-speed aircraft (Fig.1) with the fuselage 1 and wing 2, containing the triangular form of a continuous thin body 3. The dividers 7 incident flow is made of smooth sheet material (for example, by the method of cold forming, laser cutting). On each wing divider set (glued, you solder, weld) vertically (Fig.2) so that the edge 6 of the body were tight in the slot 9, protruding head portion would be parallel to the plane Q passing along the fuselage and tail sections 10 and 11 are firmly placed, respectively, to the upper 4 and lower 5 aerodynamic surfaces with the same (5-15°) or different inclination angles α and β relative to a line o-x (Fig.3-5). For example, the angle of the limb of the tail section of the divider attached to the upper aerodynamic surface, may be 5°, and the angle of the limb tail section attached to the lower aerodynamic the surface 10°.

In flight conditions of the aircraft tail sections of dividers attached to the upper aerodynamic surface of the body, increase the value of the rarefaction of air over the wing due to the deviation of the incident flow to the side of the fuselage, and the tail portions of dividers attached to the lower aerodynamic surface, increase the density (pressure) of the air flow passing under the wing, with deviation to the side of the fuselage. This increases the lifting power of the wing of the aircraft.

The invention increases the lifting force of the triangular wing aircraft.

The source of information

1. US 2576981, 1951.

1. The wing of the aircraft, containing attached to the fuselage triangular body, equipped with a vertically mounted on its edge dividers oncoming air stream, wherein each divider has a head and two tail section, and the head portion is located in front of the edge of the body parallel to the vertical plane passing along the fuselage, one of the tail sections attached to the upper aerodynamic surface of the body with the limb away from the fuselage, and the other a tail section attached to the lower aerodynamic surface of the body contour in the side of the fuselage.

2. Wing flying up the Arata, under item 1, characterized in that the angle of the limb of the tail section of the divider attached to the upper aerodynamic surface is 5-15°.

3. The wing of the aircraft, under item 1, characterized in that the angle of the limb of the tail section of the divider attached to the lower aerodynamic surface is 5-15°.



 

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