IMECH-IR  > 高温气体动力学国家重点实验室
双发动机高超声速乘波飞行器性能分析
崔凯; 高太元; 胡守超; 王秀平; 杨国伟
Source Publication高温气体动力学研究进展
2011
Pages197-202
Conference NameLHD2011夏季学术研讨会
Conference Date2011
Conference Place内蒙赤峰
Abstract当以超燃冲压发动机为动力的高超声速飞行器以马赫数大于5 的速度飞行时,激波阻力和摩擦阻力急剧增大,并引发一系列构型设计难题,除在气动方面形成所谓“升阻比屏障”外,还需满足发动机来流要求、整机推阻匹配及容积率约束等难题,同时,这些约束或需求之间还存在相互耦合和矛盾,这进一步加大了构型设计的难度。本文基于一种全参数化乘波飞行器设计方法,设计了一种双发动机模块高超声速飞行器构型,并对其进行了数值性能分析。
Keyword高超声速 乘波体 升阻比 计算流体力学
DepartmentLHD气动布局优化与计算方法
Language中文
Document Type会议论文
Identifierhttp://dspace.imech.ac.cn/handle/311007/47939
Collection高温气体动力学国家重点实验室
Recommended Citation
GB/T 7714
崔凯,高太元,胡守超,等. 双发动机高超声速乘波飞行器性能分析[C],2011:197-202.
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