矢通量分裂法在喷管超声速喷流计算中的应用  

Application of flux vector splitting method to the calculation of supersonic flow on nozzle jet

作　　者：聂赟[1] 乐贵高[1] 马大为[1] 

机构地区：[1]南京理工大学机械工程学院,南京210094

出　　处：《固体火箭技术》2013年第1期56-60,共5页Journal of Solid Rocket Technology

基　　金：国防基础科研项目(B2620110005)

摘　　要：研究了一种适用于喷管超声速喷流场的数值模拟方法。采用矢通量分裂法对喷管超声速无粘喷流场进行了数值模拟。将矢通量分裂法应用到轴对称Euler方程,并对发动机喷管尾部超声速射流进行了数值计算。计算结果与实验纹影图所反映的流动特性相吻合,与其他高精度数值格式的计算结果相比,矢通量分裂法的计算结果在轴线反射点附近具有很高分辨率,表明该方法对激波具有较好的间断捕捉能力,不会产生伪振荡或抹平现象。A numerical simulation method was discussed for the outflow field of the nozzle supersonic jet. Supersonic inviscid flow over a jet nozzle was simulated numerically using flux vector splitting method and axisymmetric Euler equations. The computa- tional results show good agreements with experimental schlieren photograph and higher resolutions at discontinuous point than those by other numerical schemes,which indicates the method has high capability to capture shock wave without numerical oscillation or artificial viscosity.

关 键 词：矢通量分裂法 超声速喷流 数值模拟 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]