RU2679104C1 - Aircraft wing - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to the aviation equipment. Wing of the aircraft consists of a center section, a console and the necessary functional systems, performed with an elongation of λ=7–11, a narrowing η=3–4.5 and a sweep χ=28–35° and contains supercritical profiles with increased sock radii. Front edge near the wing, when viewed from above, is made rectilinear, the rear edge is made with a bead. Profiles of the wing sections have a relative radius of the socks of the profiles assigned to the local chord, r≥1.0 %. Relative thickness of the profiles has a value of about 13 % in the side section and decreases to 9 % in the terminal section with a constant value in the area from 65 % of the span to the end of the wing. Wing with positive twist ε=2–2.5° in side section, end sections with negative twist ε=-2÷-3.5°, the law of the change of twist on the span has a linear descending character in the range from 20 to 100 % of the wing span.EFFECT: invention is aimed at increasing the aerodynamic quality of the aircraft, improving fuel efficiency and reducing harmful emissions into the atmosphere.1 cl, 6 dwg

Description

The present invention relates to aircraft. The invention can be used both in the development of the wings of medium- and long-haul passenger aircraft, and for the modernization of existing aircraft.

At present, when creating passenger airplanes, in addition to ensuring safety and high speed of flight, criteria of environmental impact on the environment, such as reduction of harmful emissions into the atmosphere and noise level on the ground, come to the fore. The above limitations can be achieved by improving aerodynamic perfection when creating the wings of passenger aircraft. The proposed wing is designed for operation in the cruising speed range M = 0.78-0.88.

State of the art

Various wing patterns of modern passenger aircraft are known. A typical passenger aircraft wing consists of a center section, a console and the necessary functional systems for operation at cruising numbers M = 0.78-0.88.

The wing of the Airbus Industry A-330-300 airplane is known (see Passenger Airplanes of the World, compiled by Belyaev V.V., pp. 124-125, Moscow, ASPOL, Argus 1997), made with lengthening λ = 7-11, narrowing η = 3-4.5, sweep χ _1/4 = 28-35 °, M = 0.78-0.88.

The wing of a Boeing B-777-200 aircraft is known (see Passenger Airplanes of the World, compiled by Belyaev V.V., pp. 226-227, Moscow, ASPOL, Argus 1997), made with lengthening λ = 7-11, narrowing η = 3-4.5, sweep χ _1/4 = 28-35 °, M = 0.78-0.88.

Known wing with an influx (RF Patent No. 2248303 IPC V64C 3/14, publ. 06/19/2003), made with lengthening λ = 9-11, narrowing η = 3-4.5, sweep χ _1/4 = 25-35 ° s front and rear influxes forming a profile formed as a spatial system based on the median surface, the wing inflow profile is formed with linear sections of the inserts in the bow and tail parts, which are located at the extremum points of the functions describing the coordinates of the upper and lower wing surfaces, while the length of the linear sections of the inserts is equal to the length of the sag.

The prototype of the proposed technical solution is the wing of the aircraft (Patent No. 2600413, IPC В64С 3/10, publ. 10/20/2016). The wing consists of a center section and a console. The wing is made with lengthening λ = 7-11, narrowing η = 3-4.5 and sweep χ = 25-35 ° and containing supercritical profiles. The front edge of the wing when viewed from above is straightforward and does not have a front influx. The trailing edge is made with the influx. The value of the radii of the socks of the wing sections referred to the local chord r _n. ≤0.7%, the midline of the wing profiles in shape has a concave section ranging from the nose of the profile and up to 60% of the chord to the end profiles of the wing and the limb in the tail of the profile. The shape of the upper surface of the wing sections is characterized by a long portion of small curvature in the region of 30-60% of the profile chord and the position of the maximum ordinate of the upper surface near 40% of the profile chord. The shape of the bottom surface of the profile is made with a section of strong curvature (trimming) in the tail of the profile ..

A common drawback of all the considered schemes is the deterioration of the flow around the upper surface of the wing in the root part of the wing and in the region of 25-35% of the wing span as a result of the loss of aerodynamic quality with a Mach number M≥0.8 and, as a result, a significant decrease in fuel efficiency.

SUMMARY OF THE INVENTION

The problem solved by the claimed invention is the improvement of technical, economic and technical and operational characteristics.

The technical result of the invention is to increase the aerodynamic perfection (aerodynamic quality), the bearing properties of the aircraft, at cruising flight modes and, as a result, reducing fuel consumption and reducing harmful emissions into the atmosphere, while maintaining a high cruising flight speed in the range of Mach numbers M = 0.84-0.86.

The solution of the problem and the technical result are achieved by the fact that in the swept wing, consisting of a center section, console and the necessary functional systems, it is made with lengthening λ = 7-11, narrowing η = 3-4.5 and sweep χ = 28-35 ° and containing supercritical profiles, the leading edge of the wing when viewed from above is straight, the trailing edge is made with the influx, the value of the radii of the socks of the wing profiles assigned to the local chord r _n. ≥1.0%, the relative thickness of the profiles is of the order of 13% in the side section and decreases to 9% in the end section with a practically unchanged value from 65% of the wing span to its end, the wing is designed with positive twist ε = 2-2.5˚ in the side section, end sections are designed with negative swirl ε = -2 ÷ -3.5˚, the law of change in twist in span is almost linear decreasing in the range from 20% to 100% of the wing span.

Brief Description of the Drawings

Details, features, and advantages of the present invention follow from the following description of embodiments of the claimed wing of an aircraft using the drawings, which show:

In FIG. 1 shows a General view of the swept wing,

in FIG. 2 - distribution of the relative maximum thickness along the wingspan,

in FIG. 3 - distribution of swirl along the wingspan,

in FIG. 4- typical wing profile,

in FIG. 5 - a characteristic picture of the flow around the upper surface of the wing,

in FIG. 6 - change in aerodynamic quality from the Mach number of the cruise flight and the fuel efficiency indicator K * M

The figures show the following positions in numbers:

сечений по размаху

крыла, 9 - распределение крутки крыла по размаху

крыла, 10 – сверхкритический профиль1-wing of the aircraft, 2 - center wing, 3 - wing console, 4 - leading edge of the wing, 5 - trailing edge, 6 - kink 7 - influx, 8 - thickness distribution curve

large cross-sections

wing, 9 - distribution of the wing twist in scope

wings, 10 - supercritical profile

Disclosure of invention

(8)  (Фиг. 2) сечений по размаху

крыла  от 0 до 60% вдоль размаха крыла, относительная толщина профилей имеет величину порядка 13% в бортовом сечении

и уменьшается до 9% в концевом сечении

с практически неизменным значением на участке от 65% размаха крыла и до его конца. Крыло летательного аппарата (1)   спроектировано с положительной закрученностью ε=2-2.5˚ (9) в бортовом сечении, концевые сечения спроектированы с отрицательной закрученностью ε=-2÷-3.5˚, закон изменение крутки по размаху имеет практически линейный убывающий характер в диапазоне от 20% до 100% размаха крыла (Фиг. 3).The wing of the aircraft (1) (Fig. 1) consists of a center section (2) and a console (3), made with lengthening λ = 7 ÷ 11, narrowing η = 3 ÷ 4,5 and sweep χ = 28 ÷ 35 °, without kinks along the leading edge (4) and kink (6) and influx (7) on the trailing edge (5) of the wing. The wing has a decreasing thickness distribution law.

(8) (Fig. 2) cross-sectional span

wings from 0 to 60% along the wingspan, the relative thickness of the profiles has a value of about 13% in the side section

and decreases to 9% in the end section

with a practically unchanged value in the area from 65% of the wing span to its end. The wing of the aircraft (1) is designed with positive twist ε = 2-2.5˚ (9) in the side section, the end sections are designed with negative twist ε = -2 ÷ -3.5˚, the law of change in twist in scope has an almost linear decreasing character in the range from 20% to 100% of the wingspan (Fig. 3).

The wing contains supercritical profiles (10) (Fig. 4), characterized in that the value of the radii of the socks of the wing profiles, referred to the local chord, r _n. ≥1.0%, a small modification of the wing profile was performed in the area from 60% to 100% along the chord of the wing profile in comparison with the prototype.

The wing is formed over nine basic sections obtained using a multi-stage aerodynamic design procedure, consisting of a stage of initial geometry selection, a stage of solving the inverse problem, and a stage of multi-mode optimization in 10 flight modes.

A number of design studies were carried out in the full range of cruising flight modes. The calculation results showed that the proposed wing has a continuous flow pattern (Fig. 5) of the upper surface of the wing in the entire operational range of angles of attack and Mach M.

Comparative studies of the proposed wing with the wing prototype were performed. The research results showed that the proposed wing of the aircraft compared to the prototype allows without any deterioration in aerodynamic performance to provide an additional increase in aerodynamic quality ΔKmak ≈ 0.2 ÷ 0.5 in the range of Mach numbers M = 0.82 ÷ 0.86 and fuel efficiency ΔKmakh * M ≈ 0.2 ÷ 0.4 (Fig. 6) and, as a result, reduced fuel consumption and increased flight safety.

Thus, it is possible to create an aircraft wing having the following advantages:

- high aerodynamic quality and fuel efficiency at subsonic flight speeds M _cruise = 0.78-0.88.

Claims (1)

The wing of the aircraft, consisting of a center section, a console and the necessary functional systems, is made with lengthening λ = 7-11, narrowing η = 3-4.5 and sweep χ = 28-35 ° and containing supercritical profiles, the front edge of the wing is rectilinear when viewed from above, the trailing edge is made with the influx, characterized in that the wing section profiles have the radius of the socks of the wing profiles assigned to the local chord, r _n. ≥1.0%, the relative thickness of the profiles is about 13% in the side section and decreases to 9% in the end section with a practically unchanged value from 65% of the wing span to its end, the wing is designed with positive swirl ε = 2-2.5 ° in the side section, end sections are designed with negative swirl ε = -2 ÷ -3.5 °, the law of change in twist in span has an almost linear decreasing character in the range from 20 to 100% of the wing span.

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