Optimization design for nozzle contour of rocket engine based on response surface method

被引：0
|
作者：
Wang, Yingpeng [1 ]
Xu, Yihua [1 ]
Sun, Haijun [1 ]
Feng, Xiping [2 ]
机构：
[1] Jiangxi Key Laboratory of Micro Aeroengine, School of Aircraft Engineering, Nanchang Hangkong University, Nanchang,330063, China
[2] Science and Technology on Combustion, Internal Flow and ThermoHStructure Laboratory, Northwestern Polytechnical University, Xi'an,710072, China
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2022年 / 37卷 / 01期
关键词：
Compendex;
D O I：
暂无
中图分类号：
学科分类号：
摘要：
Propulsion
引用
收藏
页码：214 / 224
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