JPH0437839Y2 - - Google Patents

Description

DETAILED DESCRIPTION OF THE INVENTION [Industrial Application Field] The present invention relates to a device for reducing induced drag to improve aircraft performance.

[Conventional technology]

Conventionally, end plates 8 and windlets 9 as shown in FIG. 4 have been attached to both ends of the main wing 1 of an aircraft in order to reduce induced resistance.

[Problem that the invention attempts to solve]

The induced resistance of an aircraft is the resistance caused by the field force (force that lifts the aircraft upward) on the main wing, and it changes depending on the planar shape of the wing body, and the aspect ratio (length-to-width ratio) as shown in Figure 3a. When the aspect ratio is large, the induced resistance is small for the same lift force, whereas when the aspect ratio is small as shown in FIG. 3b, the induced resistance is large. In order to reduce this induced resistance, conventionally a vertical plate 8 or a winglet 9 was attached to the tip of the main wing as shown in Figure 4.
These changes greatly change the external shape of the main wing, causing concerns about space during operational handling (avoiding collisions with other objects), and increasing aerodynamic loads at the ends of the main wings, causing bending of the wing root. The moment increases and reinforcement is required, resulting in an increase in weight.
This increased resistance at low angles of attack, resulting in a decline in high-speed performance.

The present invention aims to solve the above problems and reduce the induced resistance of an aircraft.

[Means for solving problems]

In the present invention, slits are provided that open on the main wing surfaces at the ends of the main wings, and the slits are connected to a high-pressure gas source so that gas is ejected from the slits in the vertical direction at the tips of the main wings.

[Effect]

High-pressure gas blows out from the slits at the ends of the main wings, and this acts like an air curtain, acting in the same way as end plates, and the vortices generated from the ends of the main wings affect the main wings. prevention and reduce induced resistance.

〔Example〕

An embodiment of the present invention will be described with reference to FIGS. 1 and 2 of the drawings.

FIG. 1 shows a sectional view, and FIG. 2 shows a plan view. At the tip of the main wing 1, there is a slit (a gap several mm wide) that extends in the chord direction of the main wing and opens on the upper and lower surfaces of the main wing.
5 is installed, high pressure gas produced by an engine 2 as a high pressure gas source attached to a main wing 1 is guided to a slit 5 through a valve 3 and a pipe 4, and high pressure gas 6 is ejected from the slit 5 in the vertical direction. The high pressure gas 6 ejected from this slit acts like an air curtain and has the same function as an end plate.
It is possible to prevent vortices generated from the tips of the main wings (trailing edge vortices) from affecting the main wing, thereby reducing induced resistance.

Furthermore, by controlling the valve 3 to appropriately control the amount of high-pressure gas ejected from the left and right wings, it can also be used for sideways maneuvering an aircraft.

In addition, as the high-pressure gas in the present invention, in addition to high-pressure gas produced by an engine, pressurized gas produced by a compressor inside an aircraft body can also be used.

Further, in the above embodiment, the gas is ejected from the slit in the vertical direction of the main wing, but the gas may be ejected in either one direction (for example, upward).

[Effect of idea]

As described above, according to this invention, high-pressure gas is ejected from the tips of the main wings, which acts like an air curtain to prevent the vortices generated from the tips of the main wings from affecting the main wings. Induced resistance can be reduced.

[Brief explanation of the drawing]

Fig. 1 is an explanatory diagram showing an elevation of one embodiment of the present invention, Fig. 2 is an explanatory diagram showing a plan view of the same embodiment, and Fig.
The figure is a plan view showing the planar shape of the main wing, and FIG. 4 is an explanatory diagram of a conventional induced drag reduction device. In the drawing, 1 is the main wing, 2 is the engine, 3 is the valve, 4 is the piping, 5 is the slit, 6 is the high pressure gas, 8
9 indicates an end plate, and 9 indicates a winglet.

Claims (1)

[Scope of utility model registration request] 1. An induced drag reduction device for an aircraft, comprising a slit provided at the end of each main wing and opening into the main wing surface, a high-pressure gas source, and piping that guides the high-pressure gas source to the slit.