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Fast prediction of flow field in scramjet combustor based on physical information neural network under wide Mach number

Xue DENG Mingming GUO Ye TIAN Yi ZHANG Erda CHEN Mengqi XU Jialing LE Hua ZHANG

中国航空学报（英文版）2025，Vol.38Issue(7)：1-24,24.

中国航空学报（英文版）2025，Vol.38Issue(7)：1-24,24.DOI:10.1016/j.cja.2025.103482

Fast prediction of flow field in scramjet combustor based on physical information neural network under wide Mach number

Xue DENG ¹Mingming GUO ¹Ye TIAN ¹Yi ZHANG ²Erda CHEN ¹Mengqi XU ¹Jialing LE ¹Hua ZHANG³

作者信息

1. Southwest University of Science and Technology,Mianyang 621000,China||Science and Technology on Scramjet Laboratory,China Aerodynamics Research and Development Center,Mianyang 621000,China
2. Science and Technology on Scramjet Laboratory,China Aerodynamics Research and Development Center,Mianyang 621000,China
3. Southwest University of Science and Technology,Mianyang 621000,China
折叠

摘要

关键词

Flow field/Intelligent prediction/Neural networks/Partial differential equations/Supersonic aircraft

Key words

Flow field/Intelligent prediction/Neural networks/Partial differential equations/Supersonic aircraft

引用本文复制引用

Xue DENG,Mingming GUO,Ye TIAN,Yi ZHANG,Erda CHEN,Mengqi XU,Jialing LE,Hua ZHANG..Fast prediction of flow field in scramjet combustor based on physical information neural network under wide Mach number[J].中国航空学报（英文版）,2025,38(7):1-24,24.

基金项目

This work was supported by the Program of Key Projects of Foundation Strengthening Plan,China(No.2022-JCJQ-ZD-114-12-03)and the Graduate Student Innovation Fund Light-house Program of Southwest University of Science and Tech-nology,China(No.24ycx3009). （No.2022-JCJQ-ZD-114-12-03）

中国航空学报（英文版）

ISSN：1000-9361

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