<p>Numerical investigation on the generation mechanism of aero-heating of rudder shaft from three-dimensional flow separation and vortices & nbsp;</p>

doi:10.1063/5.0088508

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

	Numerical investigation on the generation mechanism of aero-heating of rudder shaft from three-dimensional flow separation and vortices & nbsp;
	Lin, Mingyue 1,2; Yang, Fan 1,2; Wang, Chun 1,2
刊名	AIP ADVANCES
	2022-04-01
卷号	12 期号:4 页码:13
DOI	10.1063/5.0088508
通讯作者	Wang, Chun(wangchun@imech.ac.cn)
英文摘要	The hypersonic flow past a controlled rudder mounted at a gap to the aircraft fuselage is numerically investigated by solving three-dimensional (3D) Reynolds-averaged Navier-Stokes equations. This paper aims to explain the mechanism of production of extreme thermal environment faced by a rudder shaft from the view of physics of flow in the mounting gap. Simulations are conducted at Mach number of 10, and the gap ratio h/delta varies from 0 to 1.42, where h denotes the gap height and delta represents the thickness of the incoming turbulent boundary layer. Topological theory is utilized to identify the separation types. The formation of vortices is traced by extracting volume streamlines in the 3D space. The results indicate that the types of 3D separation appear in the gap shifts from the coexistence of horseshoe-type and tornado-type separations to only horseshoe-type separation that persists with the increase of h/delta. It is found that high heat flux is generated by the high-momentum fluid transported toward the surface by the horseshoe vortices. The tornado-type vortex prevents the incoming flow from arriving at the rudder shaft, which avoids the generation of high heat flux at the center of the rudder shaft. The rate of local heat transfer increases with h/delta as a result of the shrink and disappearance of the tornado-type vortices, which means that the region of low-speed backflow in front of the rudder is reduced and vanished. This study contributes to a clearer understanding of the flow physics in the complex disturbance area. (C) 2022 Author(s).
资助项目	National Key Research and Development Plan of China[2019YFA0405204] ; National Natural Science Foundation of China[11727901] ; National Natural Science Foundation of China[11532014]
WOS关键词	BOUNDARY-LAYER INTERACTIONS ; INDUCED SHOCK-WAVE ; SKIN-FRICTION ; SIMULATION ; TOPOLOGY ; SWEPT ; PRESSURE ; MODEL ; SHARP
WOS研究方向	Science & Technology - Other Topics ; Materials Science ; Physics
语种	英语
WOS记录号	WOS:000792498200002
资助机构	National Key Research and Development Plan of China ; National Natural Science Foundation of China
内容类型	期刊论文
源URL	[http://dspace.imech.ac.cn/handle/311007/89366]
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, Chun
作者单位	1.Univ Chinese Acad Sci, Sch Engn Sci, Beijing 100049, Peoples R China 2.Chinese Acad Sci, State Key Lab High Temp Gas Dynam, Beijing 100190, Peoples R China
推荐引用方式 GB/T 7714	Lin, Mingyue,Yang, Fan,Wang, Chun. Numerical investigation on the generation mechanism of aero-heating of rudder shaft from three-dimensional flow separation and vortices & nbsp; [J]. AIP ADVANCES,2022,12(4):13.
APA	Lin, Mingyue,Yang, Fan,&Wang, Chun.(2022). Numerical investigation on the generation mechanism of aero-heating of rudder shaft from three-dimensional flow separation and vortices & nbsp; .AIP ADVANCES,12(4),13.
MLA	Lin, Mingyue,et al." Numerical investigation on the generation mechanism of aero-heating of rudder shaft from three-dimensional flow separation and vortices & nbsp; ".AIP ADVANCES 12.4(2022):13.