RU2686784C1 - Aircraft wing - Google Patents

Abstract

FIELD: aviation.SUBSTANCE: invention relates to the aviation equipment. Wing of aircraft consists of centre section, console and required functional systems, is made with extension λ=7–11, narrowing η=3–4.5 and sweep χ=28–35° and comprises supercritical profiles with increased radii of socks. Front edge of wing at straight vertical view, rear edge is made with an influx, wing profiles are made with filling of upper surface of front part, equal to Kn=0.7–0.8 to 5 % of local chords, and with middle line on section of 10 to 40 % of local chords, having "shelf" type with ratio of corresponding ordinates of middle lines, relative thickness of profiles has value of about 15 % in onboard cross-section and decreases to 8–9 % in end section with virtually constant value on section from 65 % span of wing and to its end.EFFECT: invention is aimed at increasing aerodynamic quality of aircraft, improving fuel efficiency and reducing harmful emissions into atmosphere.1 cl, 6 dwg

Description

The technical field to which the invention relates.

The present invention relates to aircraft technology, mainly to subsonic aircraft with swept wings. The invention can be used as in the development of the wings of medium and long-haul passenger aircraft.

Prior art

Nowadays, when creating passenger planes, it is necessary to achieve many different restrictions that sometimes contradict each other. The main objectives in the design of modern wings is to increase the magnitude of the aerodynamic quality and the criterion of fuel efficiency and high speed of flight and, as a consequence, to reduce the environmental impact on the environment. 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 range of cruising speeds M = 0.78-0.88.

There are various schemes of the wings of modern passenger aircraft. A typical wing of a passenger aircraft consists of a center section, a console and the necessary functional systems for operating with cruising numbers M = 0.78–0.88.

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

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

Known wing with an influx (Patent of the Russian Federation No. 2228303 IPC W64C 3/14, published on 19.06.2003), made with an elongation λ = 9-11, narrowing η = 3-4.5, sweep χ _1/4 = 25-35 ° c front and rear overhangs forming a profile formed as a spatial system based on the middle surface, the wing overhang profile is formed with linear inserts in the nose 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 areas of inserts equal to the length of the sagging.

The prototype of the proposed technical solution is the wing of the aircraft (Patent No. 2600413, MPK VS64S 3/10, publ. 10/20/2016). The wing consists of a center section, a console. The wing is made with an elongation λ = 7-11, a narrowing η = 3-4.5 and a sweep χ = 25-35 ° and containing supercritical profiles. The front edge of the wing, when viewed from above, is rectilinear and does not have a front flow. The rear edge is made with the influx. The size of the radii of the socks of the wing sections referred to the local chord rn _. ≤0.7%, the middle line of the wing profiles has a concave section in the range from the profile toe and up to 60% of the chord to the wing end profiles and bend in the tail section of the profile. The shape of the upper surface of the wing sections is characterized by a long section of small curvature in the area 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 lower surface of the profile is made with a section of strong curvature (trimming) in the tail section of the profile.

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

Summary of 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 improve the aerodynamic quality, the criterion of fuel efficiency and as a result reduce the environmental impact on the environment, reduce emissions of harmful substances into the atmosphere, while maintaining a high cruising flight speed in the range of Mach numbers M = 0.78-0.88.

The solution of the task and the technical result is achieved by the fact that in the swept wing consisting of a center section, a console and the necessary functional systems, the extension is λ = 7-11, the restriction is η = 3-4.5 and the sweep χ = 25-35 ° and containing supercritical the profiles, the leading edge of the wing, when viewed from above, are rectilinear, the trailing edge is made with an influx, the wing profiles are made with filling the upper surface of the front part equal to Kn = 0.7-0.8 to 5% of local chords, and with the middle line in the area from 10 to 40% of local chords having a shelf "character with the ratio of the corresponding ordinates of the middle lines, the relative thickness of the profiles has a value of about 15% in the side section and decreases to 8-9% in the terminal section with a practically unchanged value from 65% of the wing span and to its end

Brief Description of the Drawings

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

FIG. 1 shows a general view of the swept wing,

in fig. 2 - typical wing profile,

in fig. 3 shows the middle lines of characteristic longitudinal sections of the wing,

in fig. 4 - the distribution of the relative maximum thickness along the wing span,

in fig. 5- characteristic pattern of the flow around the upper surface of the wing

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

In the drawings, the numbers indicate the following items:

) сечений по размаху (

) крыла.1 - swept wing of the aircraft, 2 - center section, 3 - wing console, 4 - front edge of the wing, 5 - rear edge of the wing, 6 - fracture of the rear edge of the wing, 7 - influx on the rear edge of the wing, 8 - supercritical profile, 9 - middle line of the profile, 10 - “shelving” section on the middle line of the profile, 11 - decreasing law of thickness distribution (

a) sections in scope (

) wing.

DISCLOSURE OF INVENTION

) (11) (Фиг. 4) сечений по размаху (

) крыла от 0 до 60% вдоль размаха крыла, относительная толщина профилей имеет величину порядка 15% в бортовом сечении (

=0) и уменьшается до 8-9% в концевом сечении (

=1) с практически неизменным значением на участке от 65% размаха крыла и до его конца.Swept wing (1) (Fig. 1) consisting of a center section (2) and a cantilever (3), is made with an elongation λ = 7 ÷ 11, a narrowing η = 3 ÷ 4.5 and a sweep χ = 25 ÷ 35 °, without kinks along the leading edge (4) and the fracture (6) and the influx (7) on the trailing edge (5) of the wing and supercritical profiles (8) (figure 2) with middle lines (9) which feature is the presence of the “shelving” section ( ten). The contours of the front part of the profiles (up to ≈5 local chords) have a filling ratio K _n = 0.70-0.80 (figure 3). The wing has a decreasing thickness distribution law (

) (11) (Fig. 4) sections along the span (

) wing from 0 to 60% along the span of the wing, the relative thickness of the profiles has a value of about 15% in the side section (

= 0) and decreases to 8-9% in the terminal section (

= 1) with a practically unchanged value in the area from 65% of the wing span to the end.

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

A number of computational studies were performed, in the full range of cruising flight modes. The results of the calculations showed that the proposed wing has a continuous flow around the upper surface of the wing (Fig. 5) in the entire operational range of angles of attack and Mach numbers M.

Comparative studies of the proposed wing with a wing - the prototype. The research results showed that the proposed aircraft wing compared to the prototype allows, without worsening aerodynamic parameters, to provide an additional increase in aerodynamic quality ΔKmax ≈ 0.1 ÷ 0.6 in the range of Mach numbers M = 0.78 ÷ 0.88 and fuel efficiency ΔKmax * M ≈ 0.1 ÷ 0.5 (Fig. 6) and, as a result, reduction of fuel consumption and increase in flight safety.

Thus, it is possible to create a wing of the aircraft, which has the following advantages:

- high values of the coefficients of 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 an elongation λ = 7-11, a narrowing η = 3-4.5 and a sweep χ = 28-35 ° and contains supercritical profiles, the forward edge of the wing is straight-line when viewed from above, rear edge is made with an influx, characterized in that the wing profiles are made with the filling of the upper surface of the front part equal to Kn = 0.7-0.8 to 5% of local chords, and with the middle line in the area from 10 to 40% of local chords having "shelf" character with the ratio of the corresponding ordin t midlines, the relative thickness of the profiles is of the order of 15% in the bead section and is reduced to 8-9% in the end section with a substantially constant value in the area from 65% of wing span and to its end.

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