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

压升规律可控的高超声速内收缩进气道设计
引用本文:南向军,张堃元,金志光,孙波.压升规律可控的高超声速内收缩进气道设计[J].航空动力学报,2011,26(3):518-523.
作者姓名:南向军  张堃元  金志光  孙波
作者单位:1. 南京航空航天大学,能源与动力学院,南京,210016
2. 南京理工大学,机械工程学院,航空宇航系,南京,210094
摘    要:针对高超声速内收缩进气道,以有旋特征线理论研究了一种型面压升规律可控的新型轴对称基准流场;结合流线追踪技术,以等压力梯度为例,探讨了一种圆形进口的内收缩进气道设计方法,并对三种不同压升规律的内收缩进气道性能进行了比较.结果表明,采用基准流场的内收缩进气道,能较好地保持基准流场的预定压升规律,从而拓宽了基准流场的选择范围...

关 键 词:高超声速进气道  内收缩进气道  基准流场  压升规律  数值仿真
收稿时间:2010/3/22 0:00:00
修稿时间:2010/5/28 0:00:00

Investigation on hypersonic inward turning inlets with controlled pressure gradient
NAN Xiang-jun,ZHANG Kun-yuan,JIN Zhi-guang and SUN Bo.Investigation on hypersonic inward turning inlets with controlled pressure gradient[J].Journal of Aerospace Power,2011,26(3):518-523.
Authors:NAN Xiang-jun  ZHANG Kun-yuan  JIN Zhi-guang and SUN Bo
Institution:NAN Xiang-jun1,ZHANG Kun-yuan1,JIN Zhi-guang1,SUN Bo2(1.College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China,2.Department of Aerospace Engineering,School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China)
Abstract:Axisymmetric basic flowfields with controlled pressure gradient used for hypersonic inward turning inlets were investigated using the rotational method of characteristics.In combination with streamline tracing technique,a circular inward turning inlet with the law of constant pressure gradient was designed and numerically simulated.Results show that the inward turning inlet could maintain the same law of pressure rise as its basic flowfield.Through study of the three laws of wall pressure rise,pressure grad...
Keywords:hypersonic inlet  inward turning inlet  basic flowfield  law of pressure rise  numerical simulation  
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