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Numerical method for simulating incompressible swirl flow field of aircraft with low span-chord ratio

A small aspect ratio, numerical method technology, applied in the direction of instruments, sustainable transportation, electrical digital data processing, etc., can solve the problems that the stability of convergence is uncertain and cannot be further improved

Inactive Publication Date: 2017-01-11
成都金景盛风科技有限公司
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AI Technical Summary

Problems solved by technology

[0023] 2. The spatial discrete precision of the added vorticity is limited and cannot be further improved;
[0024]3. The influence of the source term on the stability of the convergence of the numerical solution of the momentum equation is uncertain

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  • Numerical method for simulating incompressible swirl flow field of aircraft with low span-chord ratio
  • Numerical method for simulating incompressible swirl flow field of aircraft with low span-chord ratio
  • Numerical method for simulating incompressible swirl flow field of aircraft with low span-chord ratio

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Embodiment Construction

[0060] Further illustrate the numerical simulation method of the incompressible swirl field of the small aspect ratio aircraft that the present invention proposes with a specific embodiment below, this numerical simulation technique can be realized with Fortran90 computer high-level programming language, and simulates three-dimensional triangular machine by computer operation The flow field around the wing at high angle of attack and low speed flight.

[0061] In a specific embodiment, the incompressible flow field of a delta wing with a small aspect ratio at a high angle of attack is used. A large number of experiments have shown that the delta wing flies at a high angle of attack, and the flow field around it is dominated by vortex motion. The root chord length of the delta wing is c, the span is b, and the aspect ratio is 1. The calculation grid adopts multi-block structured fit hexahedral grids, O-shaped grids are used around the wing, 192 grids around the wing section di...

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Abstract

The invention discloses a numerical method for simulating an incompressible swirl flow field of an aircraft with a low span-chord ratio. Two forces in different forms are added in a momentum equation according to the characteristics of incompressible flow, so that the numerical simulation precision of a swirl motion-based flow field is improved. The forces in two forms are a helical force with vorticity in a changed gradient direction and a viscous dissipation force with vorticity in the changed gradient direction respectively. According to the method, the integral computation for computing the helical force with the vorticity in the changed gradient direction in a grid is converted into the flux computation for calculating a force on the boundary of the grid, and the spatial discretization can be enabled to have a format of high-order precision. The two forces adopt different amplification coefficients, so that the precision of the vorticity can be further kept and the swirl motion in the flow field can be simulated more accurately.

Description

technical field [0001] The invention relates to a numerical method in the field of computational fluid dynamics (CFD: Computational Fluid Dynamics), in particular to a numerical method for simulating an incompressible swirl field of an aircraft with a small aspect ratio. Background technique [0002] Computational Fluid Dynamics combines fluid mechanics, applied mathematics, and computer science, and is a subject with strong applicability. Numerical simulation of fluid mechanics problems occupies an important position in various related fields such as the exploration of the mechanism of fluid flow and the design of industrial products due to its advantages of low cost and strong intuition. One of the biggest problems and challenges facing computational fluid dynamics is how to improve the accuracy of numerical simulation, reduce errors, and faithfully represent the characteristics of fluid flow. [0003] One of the important factors affecting the accuracy of numerical simul...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 路明
Owner 成都金景盛风科技有限公司
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