Knowledge Management System of Institue of Mechanics, CAS
| Investigation on a truncated streamline-traced hypersonic Busemann inlet | |
Xiao YB(肖雅彬) ; Yue LJ(岳连捷); Gong P; Chang XY(张新宇)
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| Source Publication | 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference |
| 2008 | |
| Conference Name | 15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference |
| Conference Date | April 28, 2008 - May 1, 2008 |
| Conference Place | Dayton, OH, United states |
| Abstract | 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. |
| Keyword | Boundary Layer Corrections Busemann Inlet Core Flow Correction Method Design Points Finite Differential Methods Internal Contraction Ratio Internal Flows Mass Flow |
| Indexed By | EI |
| Language | 英语 |
| Document Type | 会议论文 |
| Identifier | http://dspace.imech.ac.cn/handle/311007/60312 |
| Collection | 力学所知识产出(1956-2008) |
| Recommended Citation GB/T 7714 | Xiao YB,Yue LJ,Gong P,et al. Investigation on a truncated streamline-traced hypersonic Busemann inlet[C]15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference,2008. |
| Files in This Item: | Download All | |||||
| File Name/Size | DocType | Version | Access | License | ||
| CaEi079.pdf（3472KB） | 会议论文 | 开放获取 | CC BY-NC-SA | View Download | ||
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