首页 | 本学科首页   官方微博 | 高级检索  
     

突跃型与平滑型斜爆震波起爆机制数值模拟
引用本文:韩旭,周进,林志勇,刘世杰. 突跃型与平滑型斜爆震波起爆机制数值模拟[J]. 航空动力学报, 2012, 27(12): 2674-2680
作者姓名:韩旭  周进  林志勇  刘世杰
作者单位:国防科学技术大学 高超声速冲压发动机技术重点实验室,长沙 410073
基金项目:国家自然科学基金(NSFC90816016,NSFC91016028)
摘    要:采用带有化学反应的Euler方程,对突跃型与平滑型2种形态的斜爆震波(ODW)在起爆机制和结构特点等方面的差异进行了研究.结果表明:斜激波(OSW)后是否存在亚声速区是判定斜爆震形态的依据.当波后火焰抬升斜激波面使得亚声速区存在时,横向激波与三波点结构就会出现并形成突跃型斜爆震.当波后所有区域皆为超声速区时,波后火焰燃烧无法影响到上游激波面,则会形成平滑型斜爆震.通过斜激波关系式给出了横向激波形成所需的临界斜激波角度,只有当斜激波角度大于此临界角度时才能形成突跃型斜爆震波,反之则形成平滑型斜爆震波. 

关 键 词:突跃型斜爆震波   平滑型斜爆震波   横向激波   三波点   起爆
收稿时间:2011-09-07

Initiation mechanism investigation of saltation and smoothness oblique detonation waves
HAN Xu,ZHOU Jin,LIN Zhi-yong and LIU Shi-jie. Initiation mechanism investigation of saltation and smoothness oblique detonation waves[J]. Journal of Aerospace Power, 2012, 27(12): 2674-2680
Authors:HAN Xu  ZHOU Jin  LIN Zhi-yong  LIU Shi-jie
Affiliation:Science and Technology on Seranjet Laboratory, National University of Defence Technology, Changsha 410073, China
Abstract:Euler equations with chemical reaction were used to study the difference in the initiation mechanism and characteristics of saltation and smoothness oblique detonation waves (ODW).The result shows that the criterion which determines the oblique detonation wave configuration is whether a subsonic zone exists behind the oblique shock wave(OSW).If the OSW raised by the flame behind it can lead to the formation of a subsonic zone, the transverse shock wave and triple point would appear and saltation ODW would form.The smoothness ODW would form if all zones are supersonic behind the OSW so the flame can not touch the upriver OSW.The OSW critical angle which leads to the formation of transverse shock wave is calculated from the equations of OSW.When the OSW angle is bigger than this critical angle, saltation ODW would form.otherwise, smoothness ODW would form.
Keywords:saltation oblique detonation waves  smoothness oblique detonation waves  transverse shock wave  triple point  detonation initiation
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