A natural laminar supercritical airfoil applied to the swept wing of medium-range civil aircraft

A swept wing, supercritical technology, applied in the direction of wing, wing shape, aircraft parts, etc., can solve the problem that the surface of the wing is difficult to maintain a large-scale natural laminar flow, etc., to improve economy and environmental protection, reduce The effect of small fuel consumption and carbon dioxide emission reduction

Active Publication Date: 2018-05-11
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0007] Aiming at the defects in the prior art, the present invention provides a natural laminar supercritical airfoil applied to the swept wing of a medium-range civil aircraft, which is used to solve the problem of the traditional natural laminar supercritical airfoil applied to the swept wing. At the same time, it is easy to induce a transition at the leading edge of the wing due to the unstable disturbance of the three-dimensional cross-flow CF wave, and it is difficult to maintain a large-scale natural laminar flow on the surface of the wing.

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  • A natural laminar supercritical airfoil applied to the swept wing of medium-range civil aircraft
  • A natural laminar supercritical airfoil applied to the swept wing of medium-range civil aircraft
  • A natural laminar supercritical airfoil applied to the swept wing of medium-range civil aircraft

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Embodiment Construction

[0034] In order to make the technical problems, technical solutions and beneficial effects solved by the present invention clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, not to limit the present invention.

[0035] Civil aircraft cruising at high subsonic speeds generally adopt a swept-back wing design to delay shock wave generation. The boundary layer of the swept wing is affected by the lateral pressure gradient, and the velocity type has a cross-flow component. The inflection point of the cross-flow velocity pattern will cause cross-flow CF wave instability. In contrast to two-dimensional TS waves, cross-flow CF wave instabilities are amplified in the region of the parabaric gradient. The existing natural laminar flow supercritical airfoils are not designed for the appl...

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Abstract

The invention provides a natural laminar-flow supercritical wing section applied to a sweepback wing of an intermediate range civil airplane. The natural laminar-flow supercritical wing section has the following pressure distribution form: a bump appears in a front edge area of an upper surface, i.e., an area with a chordwise range of 0 to 5 percent C, a pressure coefficient height of the bump is 0.05, a bump area accounts for 0.3 percent of a whole pressure distribution area, which is used for inhibiting the unstable disturbance development of a three-dimensional cross-flow CF wave; and a favorable pressure gradient is kept in an area from the back of the bump to a shock wave position, which is used for inhibiting the unstable disturbance development from a two-dimensional flow to a TS wave. The natural laminar-flow supercritical wing section has the advantages that the development of the two-dimensional TS wave disturbance and the three-dimensional cross-flow CF wave disturbance can be simultaneously inhibited, the transition of boundary laminar flow occurring in the front edge area when the wing section is arranged on the sweepback wing can be avoided, so that a relatively large-scale natural laminar flow can still be maintained on the surface of the sweepback wing, the resistance of a whole airplane can be reduced, the cruise efficiency is increased, and the consumption of fuel oil and carbon dioxide discharging can be reduced.

Description

technical field [0001] The invention belongs to the technical field of aerodynamics, and in particular relates to a natural laminar flow supercritical airfoil applied to a swept wing of a medium-range civil aircraft. Background technique [0002] Nowadays, the international community has higher and higher requirements for new passenger aircraft and transport aircraft (hereinafter referred to as civil aircraft) in terms of energy conservation and emission reduction. On the basis of existing designs, how to further reduce the resistance of civil aircraft, improve cruise efficiency, and then reduce fuel consumption and carbon dioxide emissions is becoming more and more important. At present, the use of natural laminar flow supercritical airfoil to achieve drag reduction design is one of the key technologies with great potential to achieve this goal. [0003] The design idea of ​​the traditional natural laminar supercritical airfoil is to use the weak shock wave to form a suffi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/14B64C3/36
CPCB64C3/14B64C3/36B64C2003/148
Inventor 朱震韩忠华宋文萍
Owner NORTHWESTERN POLYTECHNICAL UNIV
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