典型布局的进气道/导弹一体化性能分析

推进技术 ›› 2011, Vol. 32 ›› Issue (4): 451-454.

• 气动热力学 • 下一篇

典型布局的进气道/导弹一体化性能分析

蒋妮,王永卫,凌文辉,王健

中国航天科工集团三十一研究所,北京 100074;中国航天科工集团三十一研究所,北京 100074;中国航天科工集团三十一研究所 高超声速冲压发动机技术重点实验室,北京 100074;中国航天科工集团三十一研究所 高超声速冲压发动机技术重点实验室,北京 100074

发布日期:2021-08-15
作者简介:蒋妮(1977—),女,高工,硕士,研究领域为冲压发动机总体设计。E-mail:wyw0904@yahoo.com.cn

Integration performance analysis of typical arrangement inlet/missile

The 31st Research Inst. of CASIC, Beijing 100074, China;The 31st Research Inst. of CASIC, Beijing 100074, China;Science and Technology onScramjet Lab.,The 31st Research Inst. of CASIC,Beijing 100074,China;Science and Technology onScramjet Lab.,The 31st Research Inst. of CASIC,Beijing 100074,China

Published:2021-08-15

摘要/Abstract

摘要： 对头部进气、颌下进气、二元(两侧)进气三种典型布局的进气道/弹体一体化性能进行了计算,就阻力系数而言,颌下及头部进气优于两侧进气,升力系数则恰好相反。头部进气的流量系数最高,颌下次之,两侧进气则最差。对不同布局的总压恢复系数进行比较,颌下及两侧进气则较头部进气有好的攻角特性。

关键词: 进气道;弹体;一体化设计;性能

Abstract: This thesis calculates integration performance of frontal inlet, chin inlet, two-dimensional inlet and missile. According to the drag coefficient, chin inlet and frontal inlet are superior to two-dimensional inlet, but the lift coefficient is the opposite. The inlet mass-flow coefficient of frontal inlet is the best, the flow coefficient of two-dimensional inlet is the lowest. By comparison of inlet total pressure recovery coefficient, attack-angle performance of chin inlet and two-dimensional inlet are superior to frontal inlet. 

Key words: Inlet; Missile body; Integration design; Performance

蒋妮,王永卫,凌文辉,王健. 典型布局的进气道/导弹一体化性能分析[J]. 推进技术, 2011, 32(4): 451-454.

典型布局的进气道/导弹一体化性能分析

Integration performance analysis of typical arrangement inlet/missile

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