Aircraft wing tip

FIELD: transport.

SUBSTANCE: invention relates to aircraft engineering. 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. 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. Angle between end plate and aerofoil makes 175-180 degrees. Wing tip is arranged at 2 to 3 degrees to wing tip chord.

EFFECT: higher aerodynamic efficiency, reduced fuel consumption.

4 dwg

 

The invention relates to the field of aviation technology and can be used at the ends of the main wings of the 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 washer is not conducive to effective weakening of the terminal VI is OC. Therefore, the aerodynamic efficiency is known wingtips insufficient.

An object of the invention is to increase the aerodynamic efficiency of the wing tip with the 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.

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 and the sweep is 60-85°, having an aerodynamic surface, coupled to a terminal plate provided with additional aerodynamic swept surface of small aspect ratio, with a sharp leading edge, mounted on the external side of the airfoil at its the end, with the rear edge of the additional aerodynamic surfaces aligned with the trailing edge of the aerodynamic surface, the sock, the positioning on the front edge of the aerodynamic surface below the level of the rear edge, and the sweep is 60-85°, and the angle between the end plate and the aerodynamic surface is 175-180°, and the wing tip mounted at an angle of 2-3° with respect to the end of the wing chord.

The invention is illustrated by drawings.

Figure 1 shows the tip on 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 ending; figure 4 shows a view B.

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, mounted on the outer side of the end washers 1 at its end, while the rear edge 4 additional aerodynamic surface 2 is combined with the rear edge 5 of the end washers 1, sock 6 is located on the front edge 7 of the end washers 1 below the level of the rear edge 5, and the sweep is α=60-85°with the aerodynamic surface 8, coupled with the terminal plate 1, provided with an additional aerodynamic swept surface 9 of small aspect ratio with a sharp leading edge 10, is mounted on the outer side of the aerodynamic surface 8 at its end, while the rear edge 11 additional aerodynamic surface 9 is aligned with the rear edge 12 wind on top of the spine 8, sock 13 is located on the front edge 14 of the airfoil 8, below the level of the rear edge 12, and the sweep is β=60-85°, and the angle between the end plate 1 and the aerodynamic surface 8, is γ=175-180°, and the wing tip mounted at an angle ε=2-3° with respect to the end of the wing chord bk.

The work of the wing tips of an aircraft is based on the interaction of the field with a vertical bevel near the end of the wing. 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, breaking it into several smaller vortices intensity. The range of angles in γ=175-180° contributes to finding the limit of the washer 1 and the lower vertical aerodynamic surfaces 8, the bevels of the stream, where the inductive speed at the end of the wing close to the maximum, and the installation of the wing tip in the range of angles ε=2-3° relative to the tip chord of the wing bkcontributes to the finding in the area of the horizontal bevel flow at higher angles of attack, which is one of the factors to increase aerodynamic efficiency. At the end of the washer 1, provided with an additional wind swept over the awn 2 small aspect ratio with a sharp leading edge 3, mounted on the outer 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 additional aerodynamic surface 2 that is installed on the terminal washer 1. On the aerodynamic surface 8, with further aerodynamic swept surface 9 of small aspect ratio, with a sharp leading edge 10, is mounted on the outer side of the aerodynamic surface 8, is also formed field vertical bevels, transforming into a stable vortex flow with education conical vortex at the leading edge 10 additional aerodynamic surfaces 9 installed on aerodynamic surfaces 8. Resulting in reduced inductance and increased glide.

Thus, the proposed ending helps to ensure the maximum effect from the process of flowing of the air flow in the whole area of the effective values. This allows to increase the effective wing span, reducing induced drag created by breaking away from the end of the swept wing, the vortex, and, as a consequence, increasing the lifting force on the wing; to increase the effective wing span, almost without changing its scope; can improve t is pivnoy efficiency of the aircraft or the 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 said additional aerodynamic swept surface is aligned with the rear edge of the end plates, 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°, characterized in that the wing tip is equipped with an aerodynamic surface, which is coupled with the terminal plate provided with appropriate additional aerodynamic swept surface of small aspect ratio, with a sharp leading edge, mounted on the outer side of the aerodynamic surface at its end, while the rear edge of the additional aerodynamic surfaces aligned with the trailing edge of the aerodynamic surface, the toe is located on the front edge of the aerodynamic surface below the level of the rear edge and the sweep is 60-85°, and the angle between the end plate and the aerodynamic surface is 175-180°, and the wing tip mounted at an angle of 2-3° with respect to the end of the wing chord.



 

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