航天推进技术研究院主办
[1]张永芝,李卓,李海龙.超声速进气道流场三维数值模拟[J].火箭推进,2008,34(03):27-30.
Zhang Yongzhil,Li Zhuo,Li Hailong.Three dimension numerical simulation oi the supersonic inlet flow-field[J].Journal of Rocket Propulsion,2008,34(03):27-30.
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Zhang Yongzhil,Li Zhuo,Li Hailong.Three dimension numerical simulation oi the supersonic inlet flow-field[J].Journal of Rocket Propulsion,2008,34(03):27-30.
超声速进气道流场三维数值模拟
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
34
期数:
2008年03期
页码:
27-30
栏目:
研究与设计
出版日期:
2008-06-30
- Title:
- Three dimension numerical simulation oi the supersonic inlet flow-field
- Keywords:
- olid rocket ramjet; supersonic inlet; numerical simulation; attack angle; compression ratio
- 分类号:
- V435
- 文献标志码:
- A
- 摘要:
- 超声速进气道是固体火箭冲压发动机至关重要的部件之一，直接影响燃烧室的 燃烧及发动机性能。基于肛5方程、标准k-6双方程湍流模型，利用FLUENT软件对某型固 体火箭冲压发动机楔形超声速进气道内外流场进行了三维数值模拟。计算得到了超声速进气 道在飞行马赫数为Ma=3．5的情况下的流场性能。并在相同马赫数下。研究了等比压缩和攻角 条件下的进气道流场的分布情况。模拟结果表明：进气道的总压恢复系数和流量系数等性能 指标受到攻角的影响而发生变化。
- Abstract:
- personic inlet is one of the important part of solid rocket ramjet．The performance research of this inlet is one of the key techniques for solid rocket ramjet．The performance of supersonic inlet determines the pressure and the air flux in combustor，then affects the work of ramjet．In this paper，based on the N—s equation、standard k-6 turbulence model，FLUENT is used to simulate the cuniform air inlet of solid rocket ramjet．The flow field of air inlet at Mach number 3．5 is gained．Under the same Mach number,some researches on the performance of flow field of air inlet with attack angle and compression ratio with body are also performed．ne simulation results indicat— ed that total pressure recovery coefficient and mass flow coe佑cient of air inlet are effected by changing attack angle．
参考文献/References:
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Seramjet Module[R]．AIAA75-1212．
[2]Kumar A．Numerical Simulation of Flow Through a 2-Strut
Scramjet Inlet[J]．Journal of Propulsion and Power，1989，
5(3)：56-59．
[3]Tan J，Chen X，Yang T，et a1．Performance Research on
Solid Fuel Ramjet[R]．AIAA 20013-3607．
[4]宋文艳．超燃冲压发动机前体／进气道和隔离段气动设计
[J]．西北工业大学学报，2004，22(1)：33—37．
[5]鞠玉涛，周长省，王政时．超声速轴对称双锥进气道流场
数值模拟研究[J]．南京理工大学学报，2005，29(4)：41 l一
414．
[6]白鹏．进气道入口形状对冲压发动机性能影响数值研究
[J]．计算力学学报，2006，23(1)：71—74．
[7]韩兆林，王强．冲压发动机外压式二元进气道流场计算
与分析[J]．飞机设计，2005，(6)：11一14．
[8]李海龙．某型同冲发动机进气道流场和结构模拟仿真
部Pareto解数可以改进算法的收敛性。
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备注/Memo
收稿日期：2008-01—26；修回日期：2008—03—10。 作者简介：张永芝(1974一)，女，博士生，研究领域为固体火箭冲压发动机。
更新日期/Last Update:
1900-01-01