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Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle

A solar unmanned aerial vehicle, low Reynolds number technology, applied in the direction of wing shape, heat reduction structure, etc., can solve the problems of airfoils that cannot be used in engineering

Active Publication Date: 2015-07-01
NORTHWESTERN POLYTECHNICAL UNIV
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, the research and development of full-wing solar aircraft has not yet been carried out in China, and the corresponding airfoil is also blank.
[0004] Foreign low Reynolds number full-wing airfoils have been applied. For example, the "Helios" solar-powered UAV is not available for engineering use in China due to confidentiality reasons.

Method used

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  • Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle
  • Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle
  • Low-Reynolds-number wing section matched with full-wing solar unmanned aerial vehicle

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Embodiment Construction

[0043] This embodiment is implemented on a full-wing solar unmanned aerial vehicle.

[0044] This embodiment is used for the matching design of the inner and outer wings of a full-wing solar unmanned aerial vehicle, the design speed of the airfoil is 10 m / s, and the design Reynolds number is 2.6×10 5 , the maximum lift coefficient > 1.4, the maximum lift-to-drag ratio > 60, the moment coefficient of the airfoil within the range of 10 degrees angle of attack to keep the moment coefficient variation within ±0.01, and the moment coefficient at the reference point relative to the 1 / 4 airfoil chord length >-0.01. full wing solar drone Figure 10 and Figure 11 shown.

[0045] In order to achieve the above goals, this embodiment provides two airfoils, respectively matching the inner wing and the outer wing of the full-wing solar UAV, wherein the relative thickness of the airfoil 1 matching the inner wing is 11%, and the maximum camber is 3.48% , where the chordwise position of t...

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Abstract

The invention provides a low-Reynolds-number wing section matched with a full-wing solar unmanned aerial vehicle. The low-Reynolds-number wing section is characterized in that the relative thickness of the wing section is 11%-13%, the maximum camber of the wind section is 2%-4%, and a chordwise position with the maximum camber is 25%-30%; the wing section has a single bent outline in a 70% chordwise range from a front edge. With a full-aircraft matching design, the checking of pneumatic characteristics of a pair of wing sections is finished by checking the corresponding pneumatic characteristics of the wing sections and applying the two wing sections to the full-wing solar unmanned aerial vehicle, and the low-Reynolds-number wing section shows good pneumatic characteristics and engineering enforceability and can meet application demands on low Reynolds number, high lift force and lift-to-drag ratio and large relative thickness of the full-wing solar unmanned aerial vehicle.

Description

technical field [0001] The invention relates to the field of airfoil design in the aerodynamic shape design of an aircraft, in particular to a low Reynolds number airfoil matching a full-wing solar unmanned aerial vehicle. Background technique [0002] Compared with conventional aerodynamic aircraft, solar unmanned aerial vehicle has particularity in aerodynamic design and analysis. This type of aircraft has a low flying speed and a low flying Reynolds number. Its cruise Reynolds number is about 200,000-400,000. It mainly involves low Reynolds number, low-speed laminar flow, laminar bubbles, laminar flow separation and laminar turbulence. The physical phenomena such as the transition of the flow are very different from the flow under the medium and high Reynolds number flight conditions of conventional power. Therefore, it is determined that the aerodynamic design method and idea of ​​solar UAV are obviously different from those of medium and high Reynolds number aircraft. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C3/10B64C3/36
Inventor 周洲甘文彪王正平祝小平
Owner NORTHWESTERN POLYTECHNICAL UNIV
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