Numerical analysis on the heat transfer of three types of nozzles for the hypersonic long-run wind tunnel

被引：0
|
作者：
XING YunFei [1 ]
ZHONG FengQuan [1 ]
LI DongXia [1 ]
ZHANG XinYu [1 ]
机构：
[1] National Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences
来源：
ScienceChina(TechnologicalSciences) | 2015年 / 58卷 / 03期
基金：
中国国家自然科学基金;
关键词：
hypersonic scramjet test tunnel; nozzle; aerodynamic heating; convective heat transfer;
D O I：
暂无
中图分类号：
V211.74 [风洞];
学科分类号：
0801 ; 080103 ; 080104 ;
摘要：
The hypersonic long-run scramjet test tunnel is one of the key ground facilities for the studies of ramjet/scramjet and hypersonic thermal management.Due to the significantly large heat loading,the nozzle of the tunnel facility demands effective cooling protection.In this work,the two-dimensional,three-dimensional and axisymmetric Mach 6.5 nozzles at an inlet total temperature of 1840 K and a total pressure of 6.4 MPa were studied with main focuses on the properties of aerodynamic heating of nozzles.The present work aims to provide insights into the design of an effective cooling system for the nozzle and other components of the hypersonic long-run wind tunnel.
引用
收藏
页码：470 / 475
页数：6
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