Theories and methods for designing hypersonic high-enthalpy flow nozzles

doi:10.1016/j.cja.2021.01.018

CORC > 力学研究所 > 中国科学院力学研究所 > 高温气体动力学国家重点实验室

	Theories and methods for designing hypersonic high-enthalpy flow nozzles
	Wang, Yunpeng 2; Jiang, Zonglin 1,2
刊名	CHINESE JOURNAL OF AERONAUTICS
	2022
卷号	35 期号:1 页码:318-339
关键词	Boundary layer correction High-enthalpy flow Hypersonic wind tunnel Nozzle design Real-gas effects
ISSN号	1000-9361
DOI	10.1016/j.cja.2021.01.018
通讯作者	Wang, Yunpeng(wangyunpeng@imech.ac.cn)
英文摘要	Hypersonic high-enthalpy wind tunnels have been a challenge to ground tests in aerospace research area for decades and its test flow uniformity is one of the most important parameters for evaluating wind tunnel performances. Regarding to the performance requirement, theories and methods for designing hypersonic flow nozzles at high enthalpy conditions are quite difficult, but very interesting topics, especially when air molecule dissociations take place in wind tunnel test gas reservoirs. In this paper, fundamental theories and important methods for nozzle designs are briefly reviewed with the emphasis on two-dimensional axisymmetric nozzles for hypersonic high enthalpy wind tunnels, including the Method of Characteristics (MOC), the graphic design method, the Sivells method, the theory for boundary correction, and the CFD-based design optimization methods. These theories and methods had been proposed based on several physical issues, respectively, which play important roles in nozzle flow expansion processes. These issues cover the expansion wave generation and reflection, the boundary layer development, the real gas effect of hypersonic high-enthalpy flows. Difficulties arising from applications of these methods in hypersonic high-enthalpy nozzle design are discussed in detail and the state of the art of the nozzle design technologies that have reached for decades is summarized with some brief comments. Finally, the prospect for the hypersonic nozzle design methods, and its numerical and experimental verifications are provided with from authors' viewpoint for readers' reference.(c) 2021 Chinese Society of Aeronautics and Astronautics. Production and hosting by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).
资助项目	National Natural Science Foundation of China[11672357] ; National Natural Science Foundation of China[11727901]
WOS关键词	AERODYNAMIC DESIGN ; CONTOURED NOZZLES ; EXPLORATION ; JET
WOS研究方向	Engineering
语种	英语
WOS记录号	WOS:000788736600010
资助机构	National Natural Science Foundation of China
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/89000]
专题	力学研究所_高温气体动力学国家重点实验室
通讯作者	Wang, Yunpeng
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, Inst Mech, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Wang, Yunpeng,Jiang, Zonglin. Theories and methods for designing hypersonic high-enthalpy flow nozzles[J]. CHINESE JOURNAL OF AERONAUTICS,2022,35(1):318-339.
APA	Wang, Yunpeng,&Jiang, Zonglin.(2022).Theories and methods for designing hypersonic high-enthalpy flow nozzles.CHINESE JOURNAL OF AERONAUTICS,35(1),318-339.
MLA	Wang, Yunpeng,et al."Theories and methods for designing hypersonic high-enthalpy flow nozzles".CHINESE JOURNAL OF AERONAUTICS 35.1(2022):318-339.