高超声速层流气动热预测混合算法研究  

Study of hybrid scheme for the prediction of aerodynamic heat transfer-rate in hypersonic laminar flow

作　　者：毛枚良[1] 江定武[1] 邓小刚[1] 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2009年第3期275-280,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金-创新群体基金(10321002)

摘　　要：提出了兼顾激波和边界层模拟的混合算法——在激波区逼近NND格式,在流动光滑区逼近三阶偏置格式,采用了Steger-Warming、KFVS和Vanleer三种典型的矢通量分裂方法,对来流马赫数为10、基于头部半径的雷诺数为1×105和1×106的球头绕流的壁面热流进行了计算。计算结果表明:混合算法明显降低了热流对网格的依赖性。在此基础上完成了钝双锥和双椭球壁面热流的预测,得到了与实验测量一致性比较好的结果。A hybrid scheme, which approaches to NND scheme in the region of the shock and its vicinities, and to the 3rd linear scheme in the smooth region, was proposed with Steger-warming, KFVS and Vanleer flux splitting method. The flows past a sphere-head were simulated at mach number 10 and Reynolds numbers 1×10^5 or 1×10^6 based on the sphere radius. The results show that the hybrid scheme greatly reduced the dependence of the heat transfer rate on grid distributions. The heat transfer rates on a blunt-bicone and a double ellipsoid were also predicted with this hybrid scheme and the predicted value agreed well with the experimental data.

关 键 词：数值模拟 热流 通量分裂方法 加权插值方法 

分 类 号：O241[理学—计算数学]