External-Compression Supersonic Inlet Free from Violent Buzz

doi:10.2514/1.J057811

	External-Compression Supersonic Inlet Free from Violent Buzz
	Chen H; Tan H; Liu YZ; Zhang QF(张启帆)
通讯作者	Tan, Hui-jun(thj@263.net)
发表期刊	AIAA JOURNAL
	2019-06-01
卷号	57 期号:6 页码:2513-2523
ISSN	0001-1452
摘要	To greatly improve the supersonic inlet stability at low cost of structural weight and complexity, a novel buzz suppression strategy based on fixed-geometry air bleed is developed. It is designed to have plenty of narrow flush slots that are widely distributed along the compression surface. Using the natural pressure gradient varying with the terminal shock position, it is capable of creating self-adaptive bypass flow removal upstream of the internal duct. A strong stabilizing effect can be thus automatically produced on the subcritical flowfield by eliminating shock-induced separation and discharging excessively captured airflow. Simultaneously, the undesired air leakage at the critical regime can be naturally restricted to prevent a prohibitive performance penalty during normal operation. To verify the effectiveness, an external-compression inlet model is specially designed and carefully tested at freestream Mach numbers of 2.0 and 2.5 with an almost full exit throttle range considered (0-99.1%). Results indicate that the subcritical stable-flow range is remarkably extended from a throttle threshold of 53.7% to that of 86.4% and 73.7%, respectively, after the usage of the proposed bleed method. Moreover, intense flow instability is totally eliminated, even when the duct exit is almost closed. Further analysis reveals that the bleed flow rate at the near-critical state is not beyond 1% of the inlet flow rate for both freestream conditions. It actually causes no obvious loss of the inlet flow rate. Also, the following total pressure drop and drag increase are below 0.4%. Additionally, the observed unique buzz flow implies that the buzz origin is not necessarily limited to the two known sources, as opposed to the long-established understanding.
DOI	10.2514/1.J057811
收录类别	SCI ; EI
语种	英语
WOS记录号	WOS:000469235700025
关键词[WOS]	VORTEX GENERATORS
WOS研究方向	Engineering
WOS类目	Engineering, Aerospace
资助项目	National Natural Science Foundation of China[11532007] ; Jiangsu Province 333 Project[BRA2018031]
项目资助者	National Natural Science Foundation of China ; Jiangsu Province 333 Project
论文分区	一类/力学重要期刊
力学所作者排名	3
RpAuthor	Tan, Hui-jun
引用统计	被引频次：16[WOS] [WOS记录] [WOS相关记录]
文献类型	期刊论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/79316
专题	高温气体动力学国家重点实验室
推荐引用方式 GB/T 7714	Chen H,Tan H,Liu YZ,et al. External-Compression Supersonic Inlet Free from Violent Buzz[J]. AIAA JOURNAL,2019,57,6,:2513-2523.
APA	Chen H,Tan H,Liu YZ,&张启帆.(2019).External-Compression Supersonic Inlet Free from Violent Buzz.AIAA JOURNAL,57(6),2513-2523.
MLA	Chen H,et al."External-Compression Supersonic Inlet Free from Violent Buzz".AIAA JOURNAL 57.6(2019):2513-2523.

条目包含的文件		下载所有文件
文件名称/大小	文献类型	版本类型	开放类型	使用许可
Jp2019199.pdf（4679KB）	期刊论文	出版稿	开放获取	CC BY-NC-SA	浏览下载