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《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:

2008年03期

Page:

27-30

Research Field:

研究与设计

Publishing date:

Info

Title:

Three dimension numerical simulation oi the supersonic inlet flow-field

Author(s):

Zhang Yongzhil; Li Zhuo2; Li Hailong2

1 Inner Mongolia University of Technology，Inner Mongolia 010051，China； 2 Inner Mongolia Dynamical Machine Acedemy，Inner Mongolia 010010，China

Keywords:

olid rocket ramjet; supersonic inlet; numerical simulation; attack angle; compression ratio

PACS:

V435

DOI:

-

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．

References:

[1]Trexler C A．Inlet Performance of the Integrated Langley 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。

Memo

Memo:

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Common functions

Last Update: 1900-01-01