An optimized information preserving method for hypersonic rarefied flow simulation

CN115618699BActive Publication Date: 2026-07-21JIANGSU UNIV OF SCI & TECH
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Patents(China)
Current Assignee / Owner
JIANGSU UNIV OF SCI & TECH
Filing Date
2022-09-19
Publication Date
2026-07-21

AI Technical Summary

Technical Problem

The traditional DSMC-IP method has inaccurate calculation formats when simulating supersonic rarefied flows, and is prone to numerical divergence and stability problems. It is difficult to reflect the characteristics of supersonic flow fields, and the calculation accuracy is insufficient under high-pressure boundary conditions.

Method used

An optimized information preservation method is adopted, including flow field initialization, particle motion, boundary condition processing, particle collision, correlation term calculation, and particle number threshold method. Combined with the flux splitting method of AUSM format, the high pressure boundary processing and correlation term flux calculation are optimized to improve the stability and accuracy of numerical algorithm.

Benefits of technology

When simulating supersonic rarefied flow, the optimized information preservation method is more stable, and the real-time calculation results are consistent with the DSMC method. It has higher statistical accuracy and clear contour structure, and the calculation results are in good agreement with the experimental results.

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Abstract

The application belongs to the technical field of fluid mechanics, and is an optimized information preservation method suitable for simulating supersonic rarefied flow, which comprises the steps of flow field initialization, particle motion, boundary condition processing, collision between simulation particles, correlation term calculation, information amount statistics, and loop calculation until flow stabilization; compared with the traditional information preservation method, the numerical results of the traditional information preservation method may be abnormal and cause program crash due to inaccurate calculation format when simulating supersonic rarefied flow, and the optimized information preservation method is more stable; the real-time calculation results of the traditional information preservation method have obvious statistical dissipation, while the flow field structure of the real-time results of the optimized information preservation method is basically consistent with that of the DSMC method, but the statistical precision is higher, and the contour structure is clear and distinct; in addition, the optimized information preservation method has better statistical precision.
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