Numerical Study on Effects of Throat Ratio Parameter of Aerospike Nozzle on Rotating Detonation Combustion

被引：0
|
作者：
Liu, Si-Yuan [1 ]
Wang, Yang [1 ]
Li, Zhen-Zhen [1 ]
Teng, Hong-Hui [1 ,2 ]
Tian, Cheng [1 ]
机构：
[1] School of Aerospace Engineering, Beijing Institute of Technology, Beijing,100081, China
[2] Chongqing Innovation Center, Beijing Institute of Technology, Chongqing,401120, China
来源：
Tuijin Jishu/Journal of Propulsion Technology | 2023年 / 44卷 / 09期
关键词：
Compilation and indexing terms; Copyright 2024 Elsevier Inc;
D O I：
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学科分类号：
摘要：
Detonation - Nozzle design - Shock waves
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