Investigation on a truncated streamline-traced hypersonic Busemann inlet
文献类型：会议论文
| 作者 | Xiao YB(肖雅彬) ; Yue LJ(岳连捷); Gong P; Chang XY(张新宇)
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| 出版日期 | 2008 |
| 会议名称 | 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference |
| 会议日期 | April 28, 2008 - May 1, 2008 |
| 会议地点 | Dayton, OH, United states |
| 关键词 | Boundary layer corrections Busemann inlet Core flow Correction method Design points Finite differential methods Internal contraction ratio Internal flows Mass flow |
| 中文摘要 | A streamline-traced inlet based on the flow within the truncated Busemann inlet is designed, which has a total contraction of 7.9 and internal contraction ratio of 2.6. The boundary layer can destroy the designed flow pattern of the internal flows. Boundary layer correction that realized with the finite differential method is applied to restore the core flow to its designed pattern. CFD tools is used to investigated the flow pattern and mass flow weighted performance of the corrected inlet on its design point of Mach 5.8. Results show the reliability of the correction method and the good performance of the inlet. Copyright © 2008 by the American Institute of Aeronautics and Astronautics, Inc. |
| 收录类别 | EI |
| 会议录 | 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
 |
| 语种 | 英语 |
| 源URL | [http://dspace.imech.ac.cn/handle/311007/60312]  |
| 专题 | 力学研究所_力学所知识产出(1956-2008) |
| 推荐引用方式 GB/T 7714 | Xiao YB,Yue LJ,Gong P,et al. Investigation on a truncated streamline-traced hypersonic Busemann inlet[C]. 见:15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Dayton, OH, United states. April 28, 2008 - May 1, 2008. |
入库方式： OAI收割
来源：力学研究所
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