摘要
研究用三维特征线相容性关系的迎风差分格式，数值模拟超音速和高超音速钝体无粘绕流流场。用钝体反方法计算头激波及其波后的流场，用轴对称流特征线法确定初值面上的流动参数。
Numerical simulations of supersonic and hypersonic inviscid flow over blunt nosed bodies are investigated by an upwind scheme of the compatibility relations for the three dimensional method of characteristics. An inverse method is used to compute the flowfield behind the detached shock and the method of axisymmetric characteristics is used to determine flow parameters on the initial value surface.The results of numerical examples agree comparatively with the experimental data.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1996年第S1期72-75,共4页
Acta Aeronautica et Astronautica Sinica
关键词
特征线法
超音速流
无粘流
method of characteristics supersonic flow inviscid flow
