Vortex generator and method for delaying stall attack angle of wing with high aspect ratio

A technology of vortex generators and large aspect ratios, which is applied in the aviation field, can solve problems such as no vortex generators, and achieve the effects of increasing the maximum available lift coefficient, delaying air separation, and making up for technical gaps

Inactive Publication Date: 2020-11-06
CHENGDU AIRCRAFT INDUSTRY GROUP
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, there are no vortex generators on aircraft with large aspect ratio and small swept wings at home and abroad

Method used

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  • Vortex generator and method for delaying stall attack angle of wing with high aspect ratio
  • Vortex generator and method for delaying stall attack angle of wing with high aspect ratio
  • Vortex generator and method for delaying stall attack angle of wing with high aspect ratio

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Effect test

Embodiment 1

[0039] This embodiment proposes a vortex generator for delaying the stall angle of attack of a large aspect ratio wing, which is installed on a large aspect ratio swept wing, such as figure 1 , figure 2 , image 3 As shown, the vortex generator is a panel with a thickness of w, including an integrally connected rectangular panel part CDBI, and an arc fan-shaped right-angle panel part ACI;

[0040] The rectangular panel part CDBI is a rectangular panel, the bottom side length IB of the rectangular panel is L2, and the side side length BD is h;

[0041] The arc fan-shaped right-angled panel part ACI is connected with the rectangular panel part CDBI with a length IC of a right-angled side length IC, and the length of the other right-angled side AI not connected with the rectangular panel part CDBI is L3; the circle formed by two right-angled sides The length of the arc side AC is s; the length of the side length AB is L2+L3;

[0042] The arc side AC is divided into two sectio...

Embodiment 2

[0046] The present invention also provides a manufacturing method of a vortex generator, which is used to manufacture the above-mentioned vortex generator, such as figure 1 , figure 2 , image 3 , Figure 4 As shown, first calculate and generate the planar shape ABDC of the vortex generator; then generate a vortex generator with a thickness w according to the planar shape ABDC;

[0047] When calculating the plane shape ABDC, at first it is necessary to calculate the length h of the side length BD of the rectangular panel part CDBI, which is also the length h of the right-angled side length IC connected by the arc fan-shaped right-angled panel part ACI and the rectangular panel part CDBI; The length of h is determined according to the thickness of the boundary layer at the wing station where the vortex generator is placed, and is slightly greater than or equal to the thickness of the local boundary layer.

[0048]Further, after the value of h is calculated, the length of L2...

Embodiment 3

[0055] The present invention also provides a method for installing and using the vortex generator, which is suitable for the installation of the above-mentioned vortex generator. 10°~30°.

[0056] In order to better realize the present invention, further, when multiple vortex generators are installed at the same time, the distance between two vortex generators is set to be 2.5%-10% of the half length.

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PUM

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Abstract

The invention provides a vortex generator and a method for delaying stall attack angle of a wing with a high aspect ratio, the vortex generator is mounted on a sweepback wing with a high aspect ratio,the vortex generator is a panel with the thickness of w, and comprises a rectangular panel part CDBI and an arc fan-shaped right-angle panel part ACI which are integrally connected; through the arrangement, the effects of delaying air flow separation, delaying stall and improving the maximum available lift coefficient are achieved.

Description

technical field [0001] The invention belongs to the field of aviation, and in particular relates to a vortex generator used for delaying the stall angle of attack of a wing with a large aspect ratio. Background technique [0002] A number of vortex generators are usually installed on the wings of modern airliners, which are actually small-aspect-ratio wings installed vertically on the surface of the fuselage at a certain installation angle. The surface of the generator can generate strong wingtip vortices. This high-energy wingtip vortex can draw the high-energy fluid outside the boundary layer into the boundary layer, so that the boundary layer in the reverse pressure gradient can continue to flow after receiving additional energy. Attached to the surface of the wing without separation, delaying or inhibiting the flow separation on the upper surface of the wing, thereby delaying the stall, delaying the stall angle of attack, increasing the maximum lift coefficient, and enha...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C23/06
CPCB64C23/06Y02T50/10
Inventor 赵艳平肖良华陈瑶闫林明陈蕊夏生林冯文梁
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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