CN206569255U

CN206569255U - Wing

Info

Publication number: CN206569255U
Application number: CN201720046757.3U
Authority: CN
Inventors: 李晓亮
Original assignee: SF Technology Co Ltd
Current assignee: Fengyi Technology (Shenzhen) Co.,Ltd.
Priority date: 2017-01-16
Filing date: 2017-01-16
Publication date: 2017-10-20
Anticipated expiration: 2027-01-16

Abstract

This application discloses a kind of wing, including the multiple section aerofoil profiles being slightly arranged side by side from wing root to the wing, external surface shape of the wing with the bezier surface set up using wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles as chain of command；The slightly aerofoil profile from wing root aerofoil profile to the wing, the windup-degree of each aerofoil profile is gradually reduced, and the chord length of each aerofoil profile is gradually reduced.The application substantially improves the lift-drag ratio of complete machine, and then improve the cruising time of aircraft by limiting the torsion angle and chord length of each aerofoil profile of wing.

Description

Wing

Technical field

The disclosure relates generally to vehicle technology field, more particularly to a kind of wing.

Background technology

Wing is one of important component of aircraft, on fuselage, and its main effect is to produce lift.By current machine The influence of contour of flange, the lift of wing is inadequate, stall angle is small.

Utility model content

In view of drawbacks described above of the prior art or deficiency, expect to provide a kind of machine big with high-lift, stall angle The wing.

This application provides a kind of wing, including the multiple section aerofoil profiles being slightly arranged side by side from wing root to the wing, the wing External surface shape with the bezier surface set up using wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles as chain of command； From the wing root aerofoil profile to the wing slightly aerofoil profile, the windup-degree of each aerofoil profile is gradually reduced, and each aerofoil profile chord length gradually Reduce.

It is preferred that, from the wing root to the wing slightly provided with five section aerofoil profiles, respectively apart from the wing root aerofoil profile 0%th, 22%, 50%, 70%, 80% span distance.

It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly The torsion angle of the wing slightly aerofoil profile is followed successively by：0.5 °~1.5 °, 0.2 °~0.7 °, -0.2 °~0.2 °, -0.8 °~-0.5 °, -1.5 ° ~-1.0 °, -2.2 °~-1.2 °, -3.5 °~-2.6 °.

It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly The torsion angle of the wing slightly aerofoil profile is followed successively by：1°、0.5°、0°、-0.65°、-1.35°、-2°、-3°.

It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly The chord length of the wing slightly aerofoil profile is followed successively by：P, 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~0.55P, 0.46P~0.49P, 0.3P~0.35P.

It is preferred that, it is the wing root aerofoil profile, five section aerofoil profiles, described from direction of the wing root to the wing slightly The chord length of the wing slightly aerofoil profile is followed successively by：P、0.83P、0.75P、0.6P、0.53P、0.48P、0.33P.

Wing provided herein, by the torsion angle and chord length of each aerofoil profile for limiting wing, improves the stall of aircraft Performance, substantially improves the lift-drag ratio of complete machine, and then improve the cruising time of aircraft.

Brief description of the drawings

By reading the detailed description made to non-limiting example made with reference to the following drawings, the application's is other Feature, objects and advantages will become more apparent upon：

The front view for the wing that Fig. 1 provides for the utility model embodiment；

Fig. 2 is Fig. 1 A-A end view drawings；

Fig. 3 is Fig. 1 B-B sectional drawings；

Fig. 4 is Fig. 1 C-C sectional drawings；

Fig. 5 is Fig. 1 D-D sectional drawings；

Fig. 6 is Fig. 1 E-E sectional drawings；

Fig. 7 is Fig. 1 F-F sectional drawings；

Fig. 8 is Fig. 1 G-G end view drawings.

Embodiment

The application is described in further detail with reference to the accompanying drawings and examples.It is understood that this place is retouched The specific embodiment stated is used only for explaining relevant utility model, rather than the restriction to the utility model.Further need exist for explanation , for the ease of description, the part related to utility model is illustrate only in accompanying drawing.

It should be noted that in the case where not conflicting, the feature in embodiment and embodiment in the application can phase Mutually combination.Describe the application in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

Such as Fig. 1-Fig. 8, the wing that the utility model embodiment is provided, including be arranged side by side from wing root 1 to the wing slightly 2 it is multiple Section aerofoil profile, wing has the bezier surface set up using wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles as chain of command External surface shape；The slightly aerofoil profile from wing root aerofoil profile to the wing, the windup-degree of each aerofoil profile is gradually reduced, and the chord length of each aerofoil profile It is gradually reduced.A-A faces are the end face at wing root in Fig. 1, corresponding to wing root aerofoil profile 1-1；G-G faces are the end face that the wing is slightly located, correspondence In the wing slightly aerofoil profile 1-7.

The wing that the application is provided, forms the surface of wing by bezier surface, from wing root to the wing slightly, wing root aerofoil profile, The windup-degree of five section aerofoil profile, the wing slightly aerofoil profiles is gradually reduced, and the chord length of each aerofoil profile is gradually reduced, namely by each The restriction of aerofoil profile torsion angle and chord length so that the wing has good aeroperformance, lift is significantly improved, and reduction Resistance, therefore can improve aircraft payload using the wing and lift endurance.

Further, from wing root 1 to the wing slightly 2 provided with five section aerofoil profiles, respectively apart from wing root aerofoil profile 0%, 22%, 50%th, 70%, 80% span distance.Each slice location is a section aerofoil profile in Fig. 1, from wing root 1 between the wing slightly 2 Five section aerofoil profiles are followed successively by the first section aerofoil profile 1-2, the second section aerofoil profile 1-3, the 3rd section aerofoil profile 1-4, the 4th section wing Type 1-5, the 5th section aerofoil profile 1-6.In actual use, the aerofoil profile that aerofoil profile can be big using resistance coefficient is risen, such as from wing root to the wing Five section aerofoil profiles between slightly can be GOE227, NACA5402, NACA7403, NACA7408, NACA6401, certainly, the wing The selection of type is not limited solely to this five kinds, and the aerofoil profile of other models, five enumerated here can also be selected according to actual needs Individual is only to illustrate.Certainly according to actual needs, the section aerofoil profile of other quantity can also be set.

Further, from wing root 1 to the direction of the wing slightly 2, wing root aerofoil profile, the torsion angle α of five section aerofoil profiles, the wings slightly aerofoil profile It is followed successively by：0.5 °~1.5 °, 0.2 °~0.7 °, -0.2 °~0.2 °, -0.8 °~-0.5 °, -1.5 °~-1.0 °, -2.2 °~- 1.2 °, -3.5 °~-2.6 °.Torsion angle α mentioned here is aerofoil profile leading edge point and trailing edge point line and the angle of horizontal plane.It is logical The setting of the torsion angle is crossed, lift can be preferably lifted, resistance is reduced.

Further, from wing root 1 to the direction of the wing slightly 2, wing root aerofoil profile, the torsion angle α of five section aerofoil profiles, the wings slightly aerofoil profile It is followed successively by：1°、0.5°、0°、-0.65°、-1.35°、-2°、-3°.Torsion angle at each aerofoil profile is designed accordingly, can greatly be carried The triumph of high wing, reduces resistance.

Further, from wing root 1 to the direction of the wing slightly 2, wing root aerofoil profile, the chord length of five section aerofoil profiles, the wings slightly aerofoil profile according to It is secondary to be：P, 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~0.55P, 0.46P~0.49P, 0.3P~ 0.35P.That is, the chord length of wing root aerofoil profile is P, respectively apart from wing root aerofoil profile 0%, 22%, 50%, 70%, 80%, 100% The chord length of aerofoil profile at span distance be respectively 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~ 0.55P, 0.46P~0.49P, 0.3P~0.35P.By setting chord length, lift can be preferably lifted, resistance is reduced.

Further, from wing root 1 to the direction of the wing slightly 2, wing root aerofoil profile, the chord length of five section aerofoil profiles, the wings slightly aerofoil profile according to It is secondary to be：P、0.83P、0.75P、0.6P、0.53P、0.48P、0.33P.Chord length at each aerofoil profile is designed accordingly, can greatly be carried The triumph of high wing, reduces resistance.

Above description is only the preferred embodiment of the application and the explanation to institute's application technology principle.People in the art Member should be appreciated that utility model scope involved in the application, however it is not limited to the particular combination of above-mentioned technical characteristic Technical scheme, while should also cover in the case where not departing from utility model design, by above-mentioned technical characteristic or its be equal Feature be combined formed by other technical schemes.Such as features described above has with (but not limited to) disclosed herein The technical characteristic for having similar functions carries out technical scheme formed by replacement mutually.

Claims

1. a kind of wing, including the multiple section aerofoil profiles being slightly arranged side by side from wing root to the wing, it is characterised in that the wing has The external surface shape for the bezier surface set up using wing root aerofoil profile, the wing slightly aerofoil profile and multiple section aerofoil profiles as chain of command；

From the wing root aerofoil profile to the wing slightly aerofoil profile, the windup-degree of each aerofoil profile is gradually reduced, and the chord length of each aerofoil profile It is gradually reduced.

2. wing according to claim 1, it is characterised in that from the wing root to the wing slightly provided with five sections Aerofoil profile, respectively apart from the span distance of the wing root aerofoil profile 0%, 22%, 50%, 70%, 80%.

3. wing according to claim 2, it is characterised in that from direction of the wing root to the wing slightly, the wing root Aerofoil profile, five the section aerofoil profiles, the torsion angles of the wing slightly aerofoil profile are followed successively by：0.5 °~1.5 °, 0.2 °~0.7 °, -0.2 ° ~0.2 °, -0.8 °~-0.5 °, -1.5 °~-1.0 °, -2.2 °~-1.2 °, -3.5 °~-2.6 °.

4. wing according to claim 3, it is characterised in that from direction of the wing root to the wing slightly, the wing root Aerofoil profile, five the section aerofoil profiles, the torsion angles of the wing slightly aerofoil profile are followed successively by：1°、0.5°、0°、-0.65°、-1.35°、- 2°、-3°。

5. wing according to claim 2, it is characterised in that from direction of the wing root to the wing slightly, the wing root Aerofoil profile, five the section aerofoil profiles, the chord lengths of the wing slightly aerofoil profile are followed successively by：P, 0.80P~0.85P, 0.72~0.76P, 0.58P~0.62P, 0.5P~0.55P, 0.46P~0.49P, 0.3P~0.35P.

6. wing according to claim 5, it is characterised in that from direction of the wing root to the wing slightly, the wing root Aerofoil profile, five the section aerofoil profiles, the chord lengths of the wing slightly aerofoil profile are followed successively by：P、0.83P、0.75P、0.6P、0.53P、 0.48P、0.33P。