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Micro-nano nested groove surface drag reduction structure based on vortex drive design

A micro-nano, scale technology, used in heat-reducing structures, mechanical equipment, engine components, etc., can solve problems such as increased total resistance and difficulty in reducing resistance.

Inactive Publication Date: 2021-03-12
FUDAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
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AI Technical Summary

Problems solved by technology

However, this structure can only be adjusted in one dimension, and it is difficult to achieve the expected drag reduction effect through optimization.
When the size of the single-stage groove is large, a secondary vortex structure with a high aspect ratio is easily formed in the groove, and the increase in pressure resistance is greater than the decrease in shear stress, resulting in an increase in total resistance

Method used

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  • Micro-nano nested groove surface drag reduction structure based on vortex drive design
  • Micro-nano nested groove surface drag reduction structure based on vortex drive design
  • Micro-nano nested groove surface drag reduction structure based on vortex drive design

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Embodiment 1

[0015] Example 1 A novel micro-nano scale nested groove surface drag reduction structure designed by vortex drive

[0016] 1. Research on drag reduction mechanism of grooved surface and "vortex drive design" theory

[0017] The protrusion height theory is widely used to study the drag reduction mechanism of grooved surface structures. The protrusion height of the cross flow was first proposed by Bechert, such as figure 1 As shown, it is the distance from the top of the groove to the equivalent smooth surface of the groove through a conformal transformation. The secondary vortex structure is formed in the groove, which increases the thickness of the viscous bottom layer in the boundary layer flow, reduces the average velocity gradient near the wall surface, and reduces the surface frictional resistance. The change of vorticity distribution and flow characteristics drives the change of velocity distribution and shear stress in the groove, and the local reverse shear caused by ...

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Abstract

The invention belongs to the technical field of drag reduction surface structure design, and particularly relates to a micro-nano nested groove surface drag reduction structure based on vortex drive design. A two-stage unit group with the size smaller than that of each unit is added to the inner surface of the unit of a single-stage periodic groove structure, the two-stage unit groups are nested layers, and the nested layers are in a micro-nano scale. The micro-nano nested groove surface drag reduction structure is adopted to improve the drag reduction performance of a traditional groove surface, the structure can be applied to the design of aircraft wings or engine blades, and the friction resistance of the aircraft wings or the engine blades is reduced.

Description

technical field [0001] The invention belongs to the technical field of drag-reducing surface structure design, and in particular relates to a drag-reducing surface structure of micro-nano scale nested grooves based on vortex drive design. Background technique [0002] In recent years, drag reduction has received more and more attention because of its significance in energy saving and emission reduction. In the aircraft industry, drag reduction is an effective means to improve aircraft performance. In general, the total resistance can be broken down into two types: pressure resistance and frictional resistance. When a large air cargo plane is cruising, the frictional resistance can account for nearly 50% of the total resistance, while the frictional resistance of a small civil aircraft has a larger proportion. In addition, when determining the aerodynamic layout of civil aircraft, the reduction in pressure resistance is relatively limited, which requires attention to the re...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C3/36F01D5/14
CPCB64C3/36F01D5/147
Inventor 孙刚王立悦王聪王舒悦游波
Owner FUDAN UNIV
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