CN213008702U

CN213008702U - Drag reduction wingtip sail sheet of high aspect ratio wing

Info

Publication number: CN213008702U
Application number: CN201921998153.4U
Authority: CN
Inventors: 刘毅; 赵楠; 孟永良; 魏秦华; 赵晓霞
Original assignee: AVIC Shaanxi Aircraft Industry Group Corp Ltd
Current assignee: Shaanxi Aircraft Industry Co Ltd
Priority date: 2019-11-19
Filing date: 2019-11-19
Publication date: 2021-04-20
Anticipated expiration: 2029-11-19

Abstract

The utility model belongs to the aerodynamic configuration design technique of aircraft totality, concretely relates to big aspect ratio wing drag reduction wingtip sail piece is a device for reducing aerodynamic drag. It comprises three winglet and changeover portion, and three winglet runs through with the changeover portion respectively and is connected, and three winglet helical arrangement is from preceding to back dihedral in proper order for 45, 0, -45, adopts the utility model provides a big aspect ratio wing drag reduction wing tip sail piece, the induced resistance of subsonic speed large-scale transport plane cruising state account for about 40% of total resistance, can reduce the energy consumption of aircraft after reducing the resistance, improve economic nature, the feature of environmental protection of aircraft and have the significance.

Description

Drag reduction wingtip sail sheet of high aspect ratio wing

Technical Field

The utility model belongs to the aerodynamic configuration design technique of aircraft totality, concretely relates to big aspect ratio wing drag reduction wingtip sail piece is a device for reducing aerodynamic drag.

Background

The high aspect ratio wing drag reduction wing tip sail sheet is one kind of airplane wing tip device, and the wing tip device has several kinds, including wing tip winglet, vortex diffuser, shark fin, sail sheet, etc. the 5-year airplane has three-sheet wing tip sail sheet and has drag reduction effect.

The existing wing tip sail sheet has less research in the technical field, the early research mainly uses wind tunnel test research or simple lifting surface theory to research, the parameter optimization is insufficient, and a trial and error method is often adopted.

SUMMERY OF THE UTILITY MODEL

The technical problem to be solved is as follows: the drag reduction wing tip sail sheet is additionally arranged at the wing tip of the wing, so that the induced resistance can be effectively reduced. The induction resistance of the subsonic large-scale transport plane in the cruising state accounts for about 40% of the total resistance, and the induction resistance has important significance in reducing the energy consumption of the plane and improving the economy and the environmental protection of the plane after reducing the resistance.

Technical scheme

The utility model provides a high aspect ratio wing drag reduction wing tip sail piece has the effect that reduces induced resistance.

A drag reduction wingtip sail sheet of a high aspect ratio wing comprises three winglets and a transition section, wherein the winglets are connected with the transition section in a penetrating manner, the winglets are straight wing surfaces, a NACA4412 wing type is adopted, the dihedral angle from front to back is 45 degrees, 0 degree, -45 degrees, and the mounting angle of the winglets is determined by a CFD technology. The winglets are straight wing surfaces, NACA4412 wing shapes are adopted, each winglet is uniformly loaded at the typical flight incidence of the airplane, and the lift coefficient is 0.5.

The beneficial technical effects are as follows: adopt the utility model provides a high aspect ratio wing drag reduction wingtip sail piece, the induced resistance of subsonic large transport plane cruising state accounts for about 40% of total resistance, can reduce the energy consumption of aircraft after reducing the resistance, the economic nature that improves the aircraft, the feature of environmental protection have the significance.

Drawings

FIG. 1 is a schematic view of a drag reducing sail panel of a wing;

FIG. 2 is a side view of a drag reducing sail of a wing;

wherein: 1-a first winglet, 2-a second winglet, 3-a third winglet, 4-a transition.

Detailed Description

The utility model relates to a big aspect ratio wing drag reduction wingtip sail piece does the detailed description with the accompanying drawing:

the utility model provides a resistance-reducing wingtip sail sheet of a high aspect ratio wing, which comprises 3 winglets and 1 transition section; the 3 small wings are spirally arranged on the transition section at a reverse angle of 45 degrees from top to bottom, and the transition section is in smooth transition connection with the wingtips of the outer wings of the wings.

Specifically, the device is designed for weakening the wingtip vortex of the airplane wing by utilizing respective wingtips of 3 small-sized winglets to generate the wingtip vortex aiming at the phenomenon that the wingtip vortex of the airplane wing generates energy dissipation. The utility model provides a drag reduction wingtip sail piece comprises three winglet and a changeover portion, and wherein the sail piece section is NACA4412 wing section, chord length 1500mm, and the erection angle 0, upper and lower negative angle 45, the changeover portion passes through the fairing transition and is connected with wing wingtip, and sail piece spiral is arranged, makes each sail piece evenly loaded through the adjustment of erection angle.

The induced resistance is the additional resistance induced by generating the lift force, the airflow near the wing tip can wind from bottom to top under the action of the pressure difference, the lift force is reduced along with the airflow, and the induced resistance is generated. The wing tip vortex is a vortex formed by different flow directions of airflow of an upper wing surface and a lower wing surface at the trailing edge. The more lift generated on the wing, the stronger the tip vortex.

Wing tip devices are an advanced technology. The small wing similar to the wing airfoil is approximately vertical to the wing airfoil, and as long as the curvature and the installation direction of the wing tip winglet airfoil are properly matched with the airflow at the wing tip, the upper wing tip winglet can generate inward lateral force, so that the vortex at the wing tip can be inhibited, and the induced resistance is reduced. The single piece version of the slightly smaller airfoil is better at improving the inward deflection of the streamline on the upper surface of the airfoil, but is less effective at improving the outward deflection of the streamline on the lower surface of the airfoil. Therefore, the three winglets with different mounting angles can effectively change the lower surface streamline of the wing, reduce the vortex strength of the wing tip and reduce the induced resistance.

The utility model provides a high aspect ratio wing drag reduction wingtip sail piece, adjustment through the installation angle makes each sail piece evenly loaded, can effectually be the decline trend along with the coefficient of lift's the increase coefficient of drag of aircraft, at the aircraft state of cruising, the coefficient of lift is when 0.7, the drag reduction is about 0.0024, wingtip sail piece is no longer than under about 7% limiting condition at wing root bending moment increment, aircraft typical flight state drag reduction is about 6%, the promotion of relative wingtip extension scheme can reach 100%. Specific data are shown in table 1.

TABLE 1 drag reduction

Coefficient of lift	Drag reduction amount	Increase of bending moment of wing root
			0.4	-0.0003	5.2％
0.5	-0.0008	5.9％
			0.6	-0.0016	6.4％
0.7	-0.0024	6.7％
			0.8	-0.0034	7.0％
0.9	-0.0043	7.1％
			1	-0.0060	7.2％
1.1	-0.0090	7.2％

The utility model discloses the load that uses the geometric parameters of each wing tip sail piece, configuration mode and every winglet to be design parameter, adopts the aerodynamic force characteristic aassessment of carrying out the high accuracy based on the average Navior-Stokes (RANS) of reynolds at present mainstream, makes every winglet even loading through accurate geometric parameters adjustment, and has selected the non-dimensional lift coefficient to be 0.5, has obtained the wing tip sail piece scheme of comprehensive properties optimization.

Claims

1. The utility model provides a high aspect ratio wing drag reduction wingtip sail piece which characterized in that: the three winglets are respectively connected with the transition section in a penetrating way and are arranged spirally, and the dihedral angles of the three winglets are 45 degrees, 0 degree and-45 degrees sequentially from front to back; the transition section is connected with the wing tip of the wing through smooth transition; the winglet is a straight foil; each winglet is evenly loaded with a lift coefficient of 0.5.

2. The high aspect ratio wing drag reduction wingtip sail sheet of claim 1, wherein: the winglet employs a NACA4412 airfoil.