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Cross-scale numerical simulation method based on micro-nano groove wall surface slip effect

A numerical simulation, wall slip technology, applied in electrical digital data processing, instrumentation, computer-aided design, etc., can solve the problems of expensive calculation cost, difficult numerical simulation of global flow field, etc.

Active Publication Date: 2021-02-26
FUDAN UNIV
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Problems solved by technology

[0004] However, in the actual configuration, due to the huge scale difference between the surface structure of the micro / nano grooves and the airfoil, it is difficult to directly describe the global flow field with a large number of grids for numerical simulation, which requires expensive calculation costs

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  • Cross-scale numerical simulation method based on micro-nano groove wall surface slip effect
  • Cross-scale numerical simulation method based on micro-nano groove wall surface slip effect
  • Cross-scale numerical simulation method based on micro-nano groove wall surface slip effect

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Embodiment 1

[0040] The invention provides a cross-scale numerical simulation method based on the micro-nano groove wall slip effect.

[0041] Step (1): Regional division of the global flow field

[0042] Such as figure 1 As shown, in order to simulate the global flow field Ω of an airfoil with micro-nano grooved surface structure, we propose a domain decomposition method to solve this multi-scale problem. The global flow field is divided into the viscous bottom layer, the logarithmic layer, the outer boundary layer, and the outer flow field. The actual boundary of the flow field is Γ w , denoted with an artificial internal boundary Γ δ (within the first grid point on the wall) the microscopic near-wall region that lies within the viscous substratum. The global problem is then decomposed into two problems: 1) Based on the microscopic simulation data, the microscopic near-wall region is replaced by a proxy model of the micro-nano groove surface structure. 2) The modified wall boundar...

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Abstract

The invention belongs to the technical field of cross-scale numerical simulation, and particularly relates to a cross-scale numerical simulation method based on a micro-nano groove wall surface slip effect. The method comprises: firstly using a particle Boltzmann method considering the rarefaction effect used for simulating near-wall area flow, training a substitution model based on a large amountof simulation data, and accurately reproducing the flow characteristic of the micro-nano groove surface structure through the model; and then applying the proxy model as a corrected wall surface condition to the boundary of a macroscopic model, and performing numerical simulation on subsonic velocity and transonic velocity flow by using an RANS or LES method in macroscopic simulation, thereby providing a simulation method for flow control by applying a micro-nano groove structure in the field of aircraft design, realizing cross-scale simulation, and greatly improving calculation efficiency.

Description

technical field [0001] The invention belongs to the technical field of cross-scale numerical simulation, and in particular relates to a cross-scale numerical simulation method based on the sliding effect of micro-nano groove walls. Background technique [0002] In recent decades, in order to achieve the goal of energy saving and emission reduction, fluid mechanics scholars have been devoting themselves to the development of effective drag reduction methods in engineering applications. Inspired by the tooth-like ribs on the surface of shark skin, microscale drag-reducing structures have attracted much attention as a passive flow control technique that does not require additional equipment or energy consumption. This textured surface structure delays the transition from laminar to turbulent flow by altering the flow near the wall, thereby reducing surface friction. [0003] The micro-nano-scale groove structure infiltrates in the viscous bottom layer of the boundary layer, wh...

Claims

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Application Information

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IPC IPC(8): G06F30/28G06F113/08
CPCG06F30/28G06F2113/08Y02T90/00
Inventor 孙刚王聪王立悦王舒悦游波
Owner FUDAN UNIV
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