A method and device for optimizing the flow at the junction of a leading-edge curved flap and a leading-edge slat

A leading edge slat, optimization method technology, applied in the direction of transportation and packaging, affecting the air flow through the surface of the aircraft, aircraft parts, etc., can solve the complex flow, flow separation on the upper surface of the wing, difficult to effectively solve the leading edge flap problems such as the problem of wing flow separation, to achieve the effect of improving the maximum lift coefficient, overcoming the adverse flow interference, and promoting practical application.

Active Publication Date: 2021-07-16
中国航空研究院
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, it was found in the research that at the spanwise junction of the two leading edge flaps, due to the difference in flap type and the discontinuity of the geometric shape, complex flow phenomena will be caused, and at this position when the angle of attack increases Premature separation of flow on the upper surface of the wing
[0004] For aircraft with wing-mounted engine nacelles, the two leading edge flaps can be separated by the design of the engine pylon, but for aircraft with non-wing-mounted engines, it is currently impossible to improve the design of the engine pylon, and it is difficult to effectively solve the two flaps. Flow separation conundrum at the spanwise junction of a leading-edge flap

Method used

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  • A method and device for optimizing the flow at the junction of a leading-edge curved flap and a leading-edge slat
  • A method and device for optimizing the flow at the junction of a leading-edge curved flap and a leading-edge slat
  • A method and device for optimizing the flow at the junction of a leading-edge curved flap and a leading-edge slat

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Embodiment 1

[0046] Example 1, such as Figure 4 As shown: the overall structure of the first flow spacer not only includes the principle shape 202 of the first flow spacer itself, but also includes part of the installation structure, see the overall structure shape 401 Figure 4 The thick and short lines marked in , when the first flow spacer is actually installed, it is fixedly installed on the inner side 201 of the leading edge slat, and is retracted together with the slat. In addition, a slit slightly wider than the first flow spacer is opened on the innermost leading edge fixed section of the leading edge slat and a corresponding seal is applied; when the slat is retracted, the overall structural shape 401 of the first flow spacer will be included If the flow is no longer restrained in the slot, there may be a small arc section exposed on the lower surface of the leading edge of the wing at its lower edge, and this small arc will not have a significant impact on the flow; it can also ...

Embodiment 2

[0047] Example 2, such as Figure 5 As shown: the first flow spacer is the same as the first solution, and it is retracted together with the slat 102, so it will not be repeated. Unlike the solution in the first embodiment, in this embodiment, the second flow spacer is installed on the outer section of the leading-edge curved flap in an integrally fixed manner, and does not follow the sagging of the leading-edge curved flap 101 It can be retracted and moved, and its overall structural shape is 501 such as Figure 5 Indicated by the thick dashed lines in . In addition, the outer side of the second flow spacer is still in parallel contact with the first flow spacer installed on the innermost side of the slat or there is a small gap (for a full-scale aircraft with an average aerodynamic chord of 4.2 meters, the gap is 3 to 5 mm and can be adjusted appropriately. seal). In the flap retracted state, the overall structural shape 501 of the second flow spacer will remain on the lo...

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Abstract

The invention belongs to the technical field of flow control, and proposes a method and a device for optimizing the flow at the junction of an aeronautical wing's leading-edge curved flap and a leading-edge slat, and suppressing and delaying flow separation in this area. The present invention goes through the steps of flow field analysis, aerodynamic design, device installation, wind tunnel test, result analysis and related adjustments, and proposes to set the first flow spacer and second flow spacer. Wherein, the first flow separation sheet is located between the leading-edge curved flap and the leading-edge slat, and is arranged along the direction in which the slat extends forward; the second flow separation sheet is also located between the leading-edge curved flap and the leading edge slat. The junction of the flap and the slat is arranged along the flow direction on the lower surface of the wing. The flow optimization device of the invention effectively overcomes the unfavorable interference of the flow at the junction of the leading-edge variable flap and the leading-edge slat, delays the occurrence of flow separation on the upper surface, and improves the maximum lift coefficient of the aircraft. In addition, the invention has clear principle, simple structure, remarkable effect and has been verified by wind tunnel tests.

Description

technical field [0001] The invention belongs to the technical field of flow control, and proposes a method and a corresponding device for optimizing the flow at the junction of an aeronautical wing's leading-edge curved flap and a leading-edge slat, and suppressing and delaying flow separation in this area. Background technique [0002] With the higher requirements of green aviation for the design of new-generation aircraft, seamless leading-edge flaps that can reduce aerodynamic noise and optimize surface flow have received increasing attention. Among them, the integral drooping flap at the leading edge, which can simplify the motion mechanism, has been applied on the inner wing of the latest large civil aircraft; , can further maintain the continuous transition of the outer surface of the leading edge, which is more conducive to the realization of laminar flow wing design, so it has become a current research hotspot. [0003] In the practice of the design and research of ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C9/22B64C23/00
CPCB64C9/22B64C23/00
Inventor 钟敏华俊郑遂王浩张国鑫王钢林李小飞李岩孙侠生
Owner 中国航空研究院
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