IMECH-IR  > 力学所知识产出(1956-2008)
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)
Source Publication15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
2008
Conference Name15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Conference DateApril 28, 2008 - May 1, 2008
Conference PlaceDayton, OH, United states
AbstractA 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.
KeywordBoundary Layer Corrections Busemann Inlet Core Flow Correction Method Design Points Finite Differential Methods Internal Contraction Ratio Internal Flows Mass Flow
Indexed ByEI
Language英语
Document Type会议论文
Identifierhttp://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],2008.
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