CN2493510Y - Wing structure - Google Patents

Abstract

The utility model discloses a wing structure. The wing is in distortion shape; an angle of attack Alpha of the tip of the wing is decreased gradually in the direction of swing tip. The utility model can decrease the angle of attack of the wing in order to reduce induced drag to relatively great degree, in addition, and can also prevent the air flow of the wingtip from being separated, thereby causing wingtip stalling. The utility model has visible drag-reducing effect, greatly reduces oil consumption, and effectively improves economical efficiency.

Description

Wing structure

The utility model relates to a kind of wing structure that is used for aircraft, helicopter, cyclogyro, aerodone etc.

Wing is the major part that aircraft produces lift and resistance.Induced drag is to be accompanied by airfoil lift and a kind of flight resistance of producing.Because the existence of wing wingtip, the air that lower aerofoil pressure is big can be walked around the wing two ends and flow to the little top airfoil of pressure, like this, near the wing wingtip air is just because of flowing backward and upwards streaming the formation tip vortex that twists, the rotation of tip vortex has produced washes and following gas washing stream, the effective angle of attack of wing reduces, lift and resistance generation great change, and induced drag produces thereupon.The induced drag of dopey can account for 40% of total drag, therefore reduces induced drag gas consumption rate, the raising economy that reduces driving engine is of great importance.The measure that reduces induced drag at present mainly contains the aspect ratio of increase wing, selects suitable wing planform, installs winglet etc. additional, these measures have certain effect to drag reduction, but its drag-reduction effect is limited or negative effect is bigger, as high aspect ratio bring complex structure, strength reduction, weight increase, to negative effects such as high-speed flight are unfavorable.

The purpose of this utility model is to provide a kind of wing structure, to reduce the induced drag of aircraft.

The technical solution of the utility model is: wing is a distorted shape, and the stagger angle α of wing wing tip reduces gradually along the wingtip direction.

The angle of attack at wing tip position when the utility model reduces to fly by the stagger angle that reduces the wing tip position, near the difference of pressure of air-flow wingtip that flows through upper and lower aerofoil reduced, thereby reduce near the streaming of wingtip, suppress the generation of tip vortex, reduce air-flow on wash and under wash, reach the purpose that reduces induced drag largely.Can prevent also that in addition the wing tip air-flow from separation taking place and cause tip stall.The benefit that reduces induced drag is to improve the 1ift-drag ratio of aircraft, reduce oil consumption, improve economy.

Fig. 1 is the utility model birds-eye view;

Fig. 2 is Figure 1A-A cutaway view;

Fig. 3 is Figure 1B-B cutaway view;

Fig. 4 is Fig. 1 C-C cutaway view.

Now be further described below in conjunction with the embodiments:

Aeroplane span 15.6m, the wing mean chord length is 1.9m, the stagger angle that plays wing in the position of the terminal 1.5m of distance wing reduces by every meter 4 degree equably gradually along the wingtip direction, reduce 6 degree until wingtip, the angle of attack of the aircraft flight thriving tip on opportunity is than little 6 degree of the angle of attack of centre portion wing, and the proportion that this moment, induced drag accounted for total drag drops to very low.

Claims (1)

1, a kind of wing structure is characterized in that: described wing is a distorted shape, and the stagger angle α of wing wing tip reduces gradually along the wingtip direction.

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