Investigation on a truncated streamline-traced hypersonic Busemann inlet

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)
会议录名称	15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
	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
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.
关键词	Boundary Layer Corrections Busemann Inlet Core Flow Correction Method Design Points Finite Differential Methods Internal Contraction Ratio Internal Flows Mass Flow
收录类别	EI
语种	英语
文献类型	会议论文
条目标识符	http://dspace.imech.ac.cn/handle/311007/60312
专题	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]15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference,2008.

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