摘要
本文是针对高超声速绕流钝锥体再入飞行器，研究有烧蚀气体产物影响的化学非平衡反应粘性流ＮＳ方程数值计算方法。通过带有化学源项的ＮＳ方程对流动作数值模拟，总的连续方程由单个组元守恒方程组代替。对１３个化学组元，２６个气相化学反应，以及２个气相－固相化学反应，研究烧烛碳－空气的化学反应系统，并与纯空气化学反应系统的计算结果进行比较。利用二阶迎风ＴＶＤ差分格式和激波捕捉法。
The present study focuses on hypersonic flow over spherically blunt re entry vehicle Navier Stokes computations of hypersonic chemical nonequolibrium viscous flow with gaseous ablation products are investigated The numerical simulation technique is based on the full Navier Stokes equations with the chemical source terms The global contimuity equqtion is replaced by the individual species conservation equations The overall carbon air chemical system which consists of 13 species,26 gas phase reactions and 2 gas solid phase reactions is considered Comparisons are made with the computational results obatined in the clean air flowfield The explicit second order accurate upwind TVD scheme and shock capturing numerical algorithm are used to compute the finite rate chemically reacting blunt body flowfield
出处
《宇航学报》
EI
CAS
CSCD
北大核心
1997年第1期31-39,共9页
Journal of Astronautics
基金
国防预研基金
关键词
烧蚀气体产物
差分格式
再入飞行器
Chemical nonequilibrium viscous flow,gaseous ablation products,TVD scheme,Shock capturing numerical algorithm,hypersonic re entry vehicle
