首页 | 本学科首页   官方微博 | 高级检索  
     检索      

激波后高温高速流场中的传热特性研究
引用本文:王保国,李翔,黄伟光.激波后高温高速流场中的传热特性研究[J].航空动力学报,2010,25(5):963-980.
作者姓名:王保国  李翔  黄伟光
作者单位:1. 北京理工大学宇航学院,北京,100081
2. 北京理工大学宇航学院,北京100081;中国科学院工程热物理研究所,北京100190
基金项目:国家自然科学基金,高等学校博士学科点专项科研基金 
摘    要:激波后高温、高速流场中的热力学与传热特性分析是直接涉及到飞行器热防护设计与传热分析的关键问题之一,借助于多组分、考虑非平衡态气体的振动以及激波与热化学非平衡态效应的守恒积分型Navier-Stokes方程组,并用高分辨率总变差减小(TVD)格式进行求解,计算与研究了Apollo工程AS-202返回舱再入地球大气层的6个飞行工况(飞行马赫数15.52~22.63)以及Huygens飞行器再入土卫六大气层的6个工况(飞行马赫数17.29~24.47),分析了不同工况下弓形脱体激波后高温高速流场的热力学与传热特性,计算得到了沿壁面的热流密度分布、温度分布以及Stanton数分布,并与国外相关飞行数据进行了比较,两者吻合较好.相关计算可以指导有关飞行器的热防护设计.

关 键 词:高温传热分析  高温热化学  热防护设计  非平衡态流动  再入飞行
收稿时间:9/1/2009 12:00:00 AM
修稿时间:2009/10/13 0:00:00

Analytical study of heat transfer of high-temperature and high-velocity flow field behind shock waves
WANG Bao-guo,LI Xiang and HUANG Wei-guang.Analytical study of heat transfer of high-temperature and high-velocity flow field behind shock waves[J].Journal of Aerospace Power,2010,25(5):963-980.
Authors:WANG Bao-guo  LI Xiang and HUANG Wei-guang
Institution:School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;;School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;;School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China;Institute of Engineering Thermophysics, Chinese Academy of Sciences, Beijing 100190, China
Abstract:Analytical study of thermodynamics and heat transfer of high-temperature and high-velocity flow field behind shock waves is an important problem involving the design and heat transfer analysis of vehicle thermal protection system (TPS).The flow fields of the Apollo AS-202 return capsule aviating in the earth atmosphere of six cases (the Mach number varying from 15.52 to 22.63) and the Huygens vehicle aviating in the Titan atmosphere of six cases (the Mach number varying from 17.29 to 24.47) were simulated by using conservation integral form of Navier-Stokes equations with multi-species,nonequilibrium molecular thermal excitation and chemical reactions,based on the high-resolution total variation diminishing (TVD) scheme.Thermodynamics and heat transfer of high-temperature and high-velocity flow field behind bow shock were studied,and the wall heat flux density,wall temperature and Stanton number were in good agreement with the flight data.These results are useful for design of correlative vehicles'TPS.
Keywords:high-temperature heat transfer  high-temperature chemistry  thermal protection system(TPS)design  nonequilibrium flow  reentry flight
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号