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Numerical research on flow and performance of adaptive throat combustor for wide-range scramjet

Shengzu GUO Xu ZHANG Fangyou YU Hao CHEN Qifan ZHANG Lianjie YUE

中国航空学报（英文版）2026，Vol.39Issue(8)：213-230,18.

中国航空学报（英文版）2026，Vol.39Issue(8)：213-230,18.DOI:10.1016/j.cja.2025.103861

Numerical research on flow and performance of adaptive throat combustor for wide-range scramjet

Shengzu GUO ¹Xu ZHANG ²Fangyou YU ¹Hao CHEN ²Qifan ZHANG ²Lianjie YUE¹

作者信息

1. State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China||School of Engineering Science,University of Chinese Academy of Sciences,Beijing 100049,China
2. State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China
折叠

摘要

关键词

Geometric throat/Scramjet/Staged combustor/Thermal throat/Wide speed range

Key words

Geometric throat/Scramjet/Staged combustor/Thermal throat/Wide speed range

引用本文复制引用

Shengzu GUO,Xu ZHANG,Fangyou YU,Hao CHEN,Qifan ZHANG,Lianjie YUE..Numerical research on flow and performance of adaptive throat combustor for wide-range scramjet[J].中国航空学报（英文版）,2026,39(8):213-230,18.

基金项目

This work was supported by the National Natural Science Foundation of China(Nos.U2141220,12372236,U2341240 and 12302392). （Nos.U2141220,12372236,U2341240 and 12302392）

中国航空学报（英文版）

ISSN：1000-9361

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