固体火箭技术2013，Vol.36Issue(1)：56-60,5.DOI:10.7673/j.issn.1006-2793.2013.01.011
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
摘要
Abstract
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 computational 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Key words
flux vector splitting method/supersonic flow/ numerical simulation分类
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聂赟,乐贵高,马大为..矢通量分裂法在喷管超声速喷流计算中的应用[J].固体火箭技术,2013,36(1):56-60,5.基金项目
国防基础科研项目(B2620110005). （B2620110005）
