三维超音进气道系统流场计算的区域分裂算法  

Numerical Solution of Three Dimensional Supersonic Inlet Systems by Domain Decomposition Method

作　　者：封建湖[1] 

机构地区：[1]西北工业大学应用数学系,西安710072

出　　处：《数值计算与计算机应用》2000年第2期127-135,共9页Journal on Numerical Methods and Computer Applications

基　　金：西北工业大学"双新"计划项目!<非线性问题的教学理论方法及其应用>;航天工业总公司三院三部资助

摘　　要：computational procedure using three-dimensional Euler equations has beendeveloped to predict flows over integrated inlet systems of supersonic flighters ormissiles. The solution of 3-D Euler equations is based on finite volume spatialdiscretization and multi-step Runge-Kuttta time marching schemes proposed byJameson in 1981. In order to suppress its well-known tendency for odd-even pointdecoupling and to minimize pre- and post-shock oscillations, an adaptive dissipation term is added to the system. A non-overlapping domain decomposition technique is used to achieve the required geometric fiexibility and to relieve computermemory capacity requirement. Detailed method is given for the flux interpolationacross the interfaces between adjacent subdomains, and full solution procedure isalso presented. Numerical simulations at three flight states have been implementedfor a supersonic missile which has a complex outer shape. Satisfactory results areobtained.computational procedure using three-dimensional Euler equations has beendeveloped to predict flows over integrated inlet systems of supersonic flighters ormissiles. The solution of 3-D Euler equations is based on finite volume spatialdiscretization and multi-step Runge-Kuttta time marching schemes proposed byJameson in 1981. In order to suppress its well-known tendency for odd-even pointdecoupling and to minimize pre- and post-shock oscillations, an adaptive dissipation term is added to the system. A non-overlapping domain decomposition technique is used to achieve the required geometric fiexibility and to relieve computermemory capacity requirement. Detailed method is given for the flux interpolationacross the interfaces between adjacent subdomains, and full solution procedure isalso presented. Numerical simulations at three flight states have been implementedfor a supersonic missile which has a complex outer shape. Satisfactory results areobtained.

关 键 词：三维超音进气道系统 流场计算 区域分裂算法 

分 类 号：O246[理学—计算数学]