PARALLELIZED UPWIND FLUX SPLITTING SCHEME FOR SUPERSONIC REACTING FLOWS ON UNSTRUCTURED HYBRID MESHES  

超声速化学反应流场迎风格式数值模拟及并行计算(英文)

作　　者：王江峰[1] 伍贻兆[1] 

机构地区：[1]南京航空航天大学航空宇航学院

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2007年第3期218-224,共7页南京航空航天大学学报（英文版）

基　　金：国家自然科学基金(10402013)资助项目~~

摘　　要：A parallelized upwind flux splitting scheme for supersonic reacting flows on hybrid meshes is presented. The complexity of super/hyper-sonic combustion flows makes it necessary to establish solvers with higher resolution and efficiency for multi-component Euler/N-S equations. Hence, a spatial second-order van Leer type flux vector splitting scheme is established by introducing auxiliary points in interpolation, and a domain decomposition method used on unstructured hybrid meshes for obtaining high calculating efficiency. The numerical scheme with five-stage Runge-Kutta time step method is implemented to the simulation of combustion flows, including the supersonic hydrogen/air combustion and the normal injection of hydrogen into reacting flows. Satisfying results are obtained compared with limited references.基于有限体积迎风格式对超声速燃烧流场进行了的数值模拟。由于超声速燃烧流场绕流的复杂性,要求对多组分Euler/N-S方程求解的数值模拟方法应具有较高的计算精度及效率。本文引用辅助点方法建立了具有空间二阶精度的van Leer迎风矢通量分裂格式,并应用于超声速燃烧流场绕流的数值模拟。化学反应为氢气/空气十反应模型,采用考虑了化学反应特征时间的当地时间步长显式Runge-Kutta时间推进格式。对钝头体模型爆轰现象、后向台阶氢气喷射及二维内外流超声速燃烧流场模型进行了区域分裂技术的并行计算。计算结果与参考文献作了对比,得到了满意的结果。

关 键 词：supersonic combustion chemical reaction upwind scheme PARALLELIZATION 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]