Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack

doi:10.1063/1.3313933

	Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack
	Li XL(李新亮); Fu DX(傅德薰); Ma YW(马延文); Li XL(李新亮)
发表期刊	Physics of Fluids
	2010
卷号	22 期号:2 页码:025105-1-18
ISSN	1070-6631
摘要	The direct numerical simulation of boundary layer transition over a 5° half-cone-angle blunt cone is performed. The free-stream Mach number is 6 and the angle of attack is 1°. Random wall blow-and-suction perturbations are used to trigger the transition. Different from the authors’ previous work [Li et al., AIAA J. 46, 2899(2008)], the whole boundary layer flow over the cone is simulated (while in the author’s previous work, only two 45° regions around the leeward and the windward sections are simulated). The transition location on the cone surface is determined through the rapid increase in skin fraction coefficient (Cf). The transition line on the cone surface shows a nonmonotonic curve and the transition is delayed in the range of 0° ≤ θ ≤ 30° (θ = 0° is the leeward section). The mechanism of the delayed transition is studied by using joint frequency spectrum analysis and linear stability theory (LST). It is shown that the growth rates of unstable waves of the second mode are suppressed in the range of 20° ≤ θ ≤ 30°, which leads to the delayed transition location. Very low frequency waves VLFWs� are found in the time series recorded just before the transition location, and the periodic times of VLFWs are about one order larger than those of ordinary Mack second mode waves. Band-pass filter is used to analyze the low frequency waves, and they are deemed as the effect of large scale nonlinear perturbations triggered by LST waves when they are strong enough.The direct numerical simulation of boundary layer transition over a 5° half-cone-angle blunt cone is performed. The free-stream Mach number is 6 and the angle of attack is 1°. Random wall blow-and-suction perturbations are used to trigger the transition. Different from the authors’ previous work [ Li et al., AIAA J. 46, 2899 (2008) ], the whole boundary layer flow over the cone is simulated (while in the author’s previous work, only two 45° regions around the leeward and the windward sections are simulated). The transition location on the cone surface is determined through the rapid increase in skin fraction coefficient (Cf). The transition line on the cone surface shows a nonmonotonic curve and the transition is delayed in the range of 20° ≤ θ ≤ 30° (θ = 0° is the leeward section). The mechanism of the delayed transition is studied by using joint frequency spectrum analysis and linear stability theory (LST). It is shown that the growth rates of unstable waves of the second mode are suppressed in the range of 20° ≤ θ ≤ 30°, which leads to the delayed transition location. Very low frequency waves (VLFWs) are found in the time series recorded just before the transition location, and the periodic times of VLFWs are about one order larger than those of ordinary Mack second mode waves. Band-pass filter is used to analyze the low frequency waves, and they are deemed as the effect of large scale nonlinear perturbations triggered by LST waves when they are strong enough.
学科领域	流体力学
DOI	10.1063/1.3313933
收录类别	SCI
语种	英语
WOS记录号	WOS:000275027800024
引用统计	被引频次：109[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/311007/33062
专题	高温气体动力学国家重点实验室
通讯作者	Li XL(李新亮)
推荐引用方式 GB/T 7714	Li XL,Fu DX,Ma YW,et al. Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack[J]. Physics of Fluids,2010,22,2,:025105-1-18.
APA	Li XL,Fu DX,Ma YW,&李新亮.(2010).Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack.Physics of Fluids,22(2),025105-1-18.
MLA	Li XL,et al."Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack".Physics of Fluids 22.2(2010):025105-1-18.

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