Aircraft wing tip

FIELD: aircraft engineering.

SUBSTANCE: invention relates to aircraft engineering. Proposed wing tip has end plate with aerodynamic sweep of light elongation and sharp leading edge arranged at end plate end outer side. Tailing edge of extra aerofoil is aligned with rear edge of end plate while nose flap is located at leading edge of end plate under the level of tailing edge, sweep making 60-85 degrees. Leading edge sweep makes 60-85 degrees. Extra aerodynamic sweep of light elongation has extra sharp leading edge made at end plate inner side to make with leading edge outside end plate outer side the sweep of 76-87 degrees.

EFFECT: higher aerodynamic efficiency of wing.

3 dwg

 

The invention relates to the field of aviation technology and can be used at the ends of the wings of aircraft.

Famous wing tip of the aircraft, having an end plate provided with an additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers on the end of the [Patent RU No. 2264328, 20.11.2005, bull. No. 32].

However, the existing wing tip having an end plate provided with an additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers at its end, while the rear edge of the additional aerodynamic surfaces combined with a rear end edge of the washer, the toe is located on the front edge of the end washers below the level of the rear edge and the sweep is 60-85°, is not conducive to maximizing aerodynamic efficiency. Streamline flow of air wing is the flow of air from the bottom plane of the wing on the top, ending prevents the flow of air flow and equalize the pressure on the top and the bottom plane of the wing, weakening powerful leaf whirlwind, but using only end washers and additional aerodynamic swept poverhnostnogo lengthening with a sharp leading edge, mounted on the outer side of the end washers on the end is not conducive to effective weakening of the vortex and the most optimal form of the distribution of the lifting force. Therefore, the aerodynamic efficiency is known wingtips of the aircraft is insufficient.

The technical result of the invention is to improve the aerodynamic efficiency of the wing tips of the aircraft with the tail washer supplied with additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers at its end.

The goal of the project is achieved by the fact that the wing tip of the aircraft, having an end plate provided with an additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers at its end, while the rear edge of the additional aerodynamic surfaces combined with a rear end edge of the washer, the toe is located on the front edge of the end washers below the level of the rear edge relative to the axis of the tip chord, sweep sharp leading edge is 60-85°, more aerodynamic swept the surface of small aspect ratio are made with extra sharp p the Central edge, mounted on the inner side of the end plate and forming with a sharp leading edge, mounted on the outer side of the end washer, sweep 76-87°.

Figure 1 shows the wing tip of the aircraft from the outer side of the left end of the wing; figure 2 shows a view of A; figure 3 shows a top view of the proposed wing tips of the aircraft.

The wing tip of the aircraft is made in the following form: end washer 1, with further aerodynamic swept surface 2 small aspect ratio with a sharp leading edge 3 on the outer side and a sharp leading edge 4 on the inner side, is installed at an angle α=9° relative to the axis of the tip chord bkmounted not only external but also internal side of the end washers 1 at its end, while the rear edge 5 additional aerodynamic swept surface 2 small aspect ratio, combined with the rear edge 6 of the end washers 1, sock 7 is located on the front edge 8 of the end washers 1 below the level of the rear edge 5, and formed the sweep is β=76-87°.

The wingtips of the aircraft based on the following processes. Streamline flow of air wing is the flow of air from the bottom plane of the wing to the upper wing tip flying devices the and prevents the flow of air flow and equalize the pressure on the top and the bottom plane of the wing, weakening powerful leaf whirlwind, breaking it into several smaller vortices intensity. At the end of the washer 1, with further aerodynamic swept surface 2 small aspect ratio with a sharp leading edge 3 on the outer side and a sharp leading edge 4 on the inner side of the end washers 1, there is formed a field of vertical bevels, transforming into a stable vortex flow with education conical vortex at the leading edge 3 on the outer side and the front edge 4 from the inner side additional aerodynamic surface 2 that is installed on the terminal washer 1. Thereby increasing the aerodynamic efficiency of the wing tips of the aircraft.

Thus, in comparison with the prototype, the proposed wing tip of the aircraft allows to provide the maximum effect from the process of flowing of the air flow in the whole area of the effective values. Increasing the aerodynamic efficiency of the wing tips of the aircraft allows to increase the effective wing span, reducing induced drag created by breaking away from the end of the swept wing vortex and, as a consequence, increasing the lifting force on the wing; to increase the effective wing span, almost without changing its scope; it allows to improve the top is positive efficiency in aircraft and flight range.

The wing tip of the aircraft, having an end plate provided with an additional aerodynamic swept surface of small aspect ratio with a sharp leading edge, mounted on the outer side of the end washers at its end, while the rear edge of the additional aerodynamic surfaces combined with a rear end edge of the washer, the toe is located on the front edge of the end washers below the level of the rear edge relative to the axis of the tip chord, sweep sharp leading edge is 60-85°, characterized in that the additional aerodynamic swept surface of small aspect ratio are made with extra sharp leading edge, mounted on the inner side of the end plate and forming with a sharp leading edge, mounted on the outer side of the end washer, sweep 76-87°.



 

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