IMECH-IR  > 高温气体动力学国家重点实验室
Iso-contraction-ratio methodology for the design of hypersonic inward turning inlets with shape transition
Xiao YB(肖雅彬); Yue LJ(岳连捷); Chen LH(陈立红); Zhang XY(张新宇); Xiao YB(肖雅彬)
Source Publication18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
2012
Conference Name18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012
Conference DateSEP 24-28, 2012
Conference PlaceTours, France
AbstractA methodology has been devised for the design of the three-dimensional hypersonic inlets with shape transition. This methodology split the objective three dimensional flowfield into a number of stream tubes, each of which has the contraction ratio that equals to the total contraction ratio of the inlet. Each stream tube is regarded as a portion of an axisymmetric supersonic flowfield designed with computational optimization. All the stream tubes are assembled through a pressure matching process to form the objective three dimensional flowfiled and the inlet surfaces. Computational results show that the inlet has a mass capture of 0.995 at design point of Mach 5.4 and 0.952 at Mach 3.5. The uniformity of flowfield inside the inlet is shown to be quite acceptable.rights reserved.
DepartmentLHD高超声速推进技术
Funding OrganizationAmerican Institute for Aeronautics and Astronautics (AIAA)
ISBN9781600869310
Indexed ByEI
Language英语
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/48282
Collection高温气体动力学国家重点实验室
Corresponding AuthorXiao YB(肖雅彬)
Recommended Citation
GB/T 7714
Xiao YB,Yue LJ,Chen LH,et al. Iso-contraction-ratio methodology for the design of hypersonic inward turning inlets with shape transition[C]18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012,2012.
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