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High-altitude, low-speed and high-lift natural laminar flow airfoil

A high-lift wing and airfoil technology, applied in the direction of the wing shape, can solve the problems that are not suitable for drones, and achieve the effects of small airfoil resistance, large airfoil lift-to-drag ratio, and ease of stall characteristics

Active Publication Date: 2016-07-13
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

However, the above two patent applications are mainly designed for high-speed flows with a Mach number of around 0.6, not for high-altitude low-speed and low Reynolds number conditions. That is to say, the airfoils disclosed in the above-mentioned two patent applications are not suitable for high-altitude long Airtime UAV

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  • High-altitude, low-speed and high-lift natural laminar flow airfoil

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[0035] 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.

[0036] Under the condition of low Reynolds number, the surface laminar flow separation phenomenon of the conventional airfoil is serious, the lift-drag characteristics of the airfoil are seriously deteriorated, and in the state of high lift, it has a large nose-down moment; while the laminar airfoil has a large The range of laminar flow leads to a large reverse pressure gradient in the tail pressure recovery, which is easy to cause separation of the trailing edge. Therefore, the design of the laminar flow airfoil is still a technical difficulty. The existing relevant pat...

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Abstract

The invention provides a high-altitude, low-speed and high-lift natural laminar flow airfoil. The maximum thickness of the airfoil is 14%C, the maximum thickness location is 36%C, the thickness of a trailing edge is 0.425%C, the maximum camber is 5.1%C, and the maximum camber location is 47%C, wherein C is the chord length of the airfoil. The airfoil firstly turns and then separates under the conditions of low speed and 1 million magnitude Reynolds numbers, laminar flow separation bubbles are not formed, and the natural laminar flow airfoil has a higher design lift coefficient and a larger lift-drag ratio, has mild stalling characteristics and good torque characteristics and can meet the performance demands of a high-altitude long-endurance unmanned aerial vehicle.

Description

technical field [0001] The invention belongs to the technical field of UAV airfoil design, in particular to a high-altitude low-speed natural laminar flow high-lift airfoil. Background technique [0002] High-altitude long-endurance drones refer to drones that fly at an altitude of more than 18,000 meters and have a continuous flight time of more than one day. The aerodynamic design of high-altitude and long-endurance UAVs has many differences from other types of UAVs, including: (1) High-altitude and long-endurance UAVs require a high lift-to-drag ratio to maintain a relatively high lift-to-drag ratio. Long cruising flight time, smooth execution of communication, high-altitude monitoring and other tasks. Therefore, this type of UAV generally adopts a large aspect ratio, small sweep or straight wing; use a thick airfoil to ensure that the wing provides sufficient space to load more fuel. (2) One of the most basic aerodynamic problems of high-altitude flight is that the air...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/14
CPCB64C3/14
Inventor 韩忠华张瑜史来祥许建华宋文萍
Owner NORTHWESTERN POLYTECHNICAL UNIV
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