Knowledge Management System of Institue of Mechanics, CAS
| Direct Numerical Simulation Of Hypersonic Boundary-Layer Transition Over A Blunt Cone | |
Li XL(李新亮) ; Fu DX(傅德薰); Ma YW(马延文); Li, XL (reprint author), Chinese Acad Sci, Inst Mech, Lab Nonlinear Mech, Beijing 100080, Peoples R China.
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| Source Publication | AIAA Journal
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| 2008 | |
| Pages | 2899-2913 |
| ISSN | 0001-1452 |
| Abstract | Direct numerical simulation of transition How over a blunt cone with a freestream Mach number of 6, Reynolds number of 10,000 based on the nose radius, and a 1-deg angle of attack is performed by using a seventh-order weighted essentially nonoscillatory scheme for the convection terms of the Navier-Stokes equations, together with an eighth-order central finite difference scheme for the viscous terms. The wall blow-and-suction perturbations, including random perturbation and multifrequency perturbation, are used to trigger the transition. The maximum amplitude of the wall-normal velocity disturbance is set to 1% of the freestream velocity. The obtained transition locations on the cone surface agree well with each other far both cases. Transition onset is located at about 500 times the nose radius in the leeward section and 750 times the nose radius in the windward section. The frequency spectrum of velocity and pressure fluctuations at different streamwise locations are analyzed and compared with the linear stability theory. The second-mode disturbance wave is deemed to be the dominating disturbance because the growth rate of the second mode is much higher than the first mode. The reason why transition in the leeward section occurs earlier than that in the windward section is analyzed. It is not because of higher local growth rate of disturbance waves in the leeward section, but because the growth start location of the dominating second-mode wave in the leeward section is much earlier than that in the windward section. |
| Keyword | Hyperbolic Conservation-laws |
| DOI | 10.2514/1.37305 |
| Indexed By | SCI ; EI |
| Language | 英语 |
| WOS ID | WOS:000260817900024 |
| WOS Keyword | HYPERBOLIC CONSERVATION-LAWS ; FLAT-PLATE ; TURBULENT SPOTS ; WENO SCHEME ; RECEPTIVITY ; WAVES ; FLOW ; DISTURBANCES ; STABILITY |
| WOS Research Area | Engineering |
| WOS Subject | Engineering, Aerospace |
| Citation statistics | |
| Document Type | 期刊论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/25846 |
| Collection | 力学所知识产出(1956-2008) |
| Corresponding Author | Li, XL (reprint author), Chinese Acad Sci, Inst Mech, Lab Nonlinear Mech, Beijing 100080, Peoples R China. |
| Recommended Citation GB/T 7714 | Li XL,Fu DX,Ma YW,et al. Direct Numerical Simulation Of Hypersonic Boundary-Layer Transition Over A Blunt Cone[J]. AIAA Journal,2008:2899-2913. |
| APA | 李新亮,傅德薰,马延文,&Li, XL .(2008).Direct Numerical Simulation Of Hypersonic Boundary-Layer Transition Over A Blunt Cone.AIAA Journal,2899-2913. |
| MLA | 李新亮,et al."Direct Numerical Simulation Of Hypersonic Boundary-Layer Transition Over A Blunt Cone".AIAA Journal (2008):2899-2913. |
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