SFD方法模拟高超声速进气道中激波与边界层干扰

推进技术 ›› 2000, Vol. 21 ›› Issue (1): 15-19.

SFD方法模拟高超声速进气道中激波与边界层干扰

张树道,司徒明,韩肇元

航天机电集团公司31所!北京100074;航天机电集团公司31所!北京100074;中国科学技术大学力学与机械工程系!安徽合肥230026

发布日期:2021-08-15
基金资助:
国家自然科学基金资助项目! ( 19882 0 0 4 )

SFD method simulation on interactions of shock waves with boundary layers in the hypersonic inlet

The 31st Research Inst ,Beijing 100074,China;The 31st Research Inst ,Beijing 100074,China;Dept of Mechanics and Mechanical Engineering,China Univ of Science and Technology, Hefei 230026,China

Published:2021-08-15

摘要/Abstract

摘要： 采用SFD方法,在EXCEL软件上利用NND格式数值模拟了激波与平板边界层之间的相互作用以及激波与管道壁面边界层的相互作用,即高超声速进气道隔离段内激波串流动现象。该方法的特点是简单、直观而且不用常规编程,计算结果基本反映了流场的基本结构,表明SFD方法可能是一种具有潜力的计算方法。

关键词: 高超声速进气道;进气气流;激波;激波边界层干扰;计算流体动力学;数值计算

Abstract: The interactions of shock waves with boundary layers on the flat plate and shock chains in the isolator of the hypersonic inlet were numerically simulated respectively by the method of Spreadsheet Fluid Dynamics (SFD) in the EXCEL software with NND algorithm The SFD method is simple and demands no ordinary program processing The numerical results reflected the general structure of the flow field which means that SFD may be a potent computational fluid dynamics method

Key words: Hypersonic inlet;Inlet flow;Shock wave;Shock wave boundary layer interference;Computational fluid dynamics

张树道,司徒明,韩肇元. SFD方法模拟高超声速进气道中激波与边界层干扰[J]. 推进技术, 2000, 21(1): 15-19.