JPH0232000A - High-lift wing - Google Patents

Abstract

PURPOSE:To make it possible to generate lifting force without any break away until a large angle of incidence, by arranging many small dents on a wing surface, for generating vortex by dents and giving energy to a flow along a wing. CONSTITUTION:Plural lines of many small dents 3 are provided on the rear part of the upper surface of a flap 2 which extends backward from near the rear edge of a main wing 1, dents 3 are arranged on upper surface of the flap 2 in a way that plural number of dents 3a forming the first line from the front, plural number of dents 3b forming the second line,.... Dents in adjacent lines are shifted by a half pitch from each other and arranged in a zigzag. And by small vortexes generated by many dents 3, energy is given to the flow above the flap 2 and break away of the flow is prevented. Therefore, even when the angle of incidence of the flap 2 becomes big, break away of the flow is prevented from occurring and a high-lift can be obtained.

Description

[Detailed Description of the Invention] [Field of Industrial Application] The present invention is for generating a large lift force on an object flying in a fluid! (Including movable wings, the same applies hereinafter) (Regarding.

[Conventional technology]

Conventional technology includes wings with normal smooth surfaces. These wing surfaces were smooth and had no irregularities.

[Problem to be solved by the invention]

In conventional maples with smooth surfaces, when the angle of attack increases, the flow separates and no more lift is generated. This is because the flow on the wing loses energy due to rapid deceleration.

The present invention aims to provide a wing that can prevent flow separation and provide high lift.

[Failure to solve the problem]

In the present invention, a large number of small depressions are arranged on the wing surface.

[Last month]

In the present invention, each small depression on the wing surface generates a small vortex that imparts energy to the flow along the wing surface. In this way, the fluid can withstand rapid deceleration due to the energy input from the vortices in the depression, and continues to flow along the wing surface without separation even at large angles of attack, and continues to generate lift.

〔Example〕

Embodiments of the present invention will be described with reference to FIGS. 1 and 2.

In this embodiment, a large number of small h depressions 3 are formed in the rear part of the upper surface of the flap 2 extending rearward from near the trailing edge of the main wing 1.
has been established.

As shown in FIG. 2, the depressions 3 form a first row from the front 'P! ! A number of depressions 3a, a plurality of depressions 3b forming a second row, . . . are arranged on the upper surface of the flag 2.

The recesses 3 are hemispherical with a diameter of 3 to 5 cm and a depth of 1 to 2 cm, and the interval (L (see Figure 2)) between the recesses in each row is 3 to
The pitches are equal to five, and the recesses in adjacent rows are staggered by a half pitch.

In this embodiment, energy is imparted to the flow on the flap 2 by small vortices generated by the large number of depressions 3, and separation of the flow is prevented.

Thereby, even if the angle of attack of the flaps 2 becomes large, separation of the flow is prevented, and the high lift force can be maintained.

Although the above embodiment has a recess in the flap, the present invention is not limited to this, and can be widely applied to other movable wings such as ailerons, or fixed wings such as main wings that generate lift. can do.

In addition, the shape, size, arrangement, etc. of the depressions are not limited to those shown in the above embodiments, and the position where the depressions are provided can also prevent flow separation, such as providing the depressions on the entire surface or the front half of the upper surface of the blade. Needless to say, it can be selected as appropriate from the viewpoint of

〔Effect of the invention〕

In the present invention, a large number of small depressions arranged on the wing surface prevent separation of flow on the wing surface, and it is possible to generate a large lift force.

[Brief explanation of the drawing]

FIG. 1 is a perspective view of an embodiment of the present invention, and FIG. 2 is an enlarged view of the main parts thereof.

Claims (1)

[Claims] A high-lift wing characterized by a large number of small depressions arranged on the wing surface.