摘要
以微钝尖锥为飞行器前缘模型,采用基于分子运动论的DSMC方法模拟不同前缘曲率半径的尖锥在高超声速来流下的气动热环境,计算驻点热流率,并与Fay-Riddell公式和其他修正理论作对比,研究具有局部稀薄气体效应的高超声速尖锥气动加热特征及其变化规律.发现修正的Cheng参数适合作为工程上判断驻点区域稀薄气体效应影响大小的判据.
A small nose sphere-cone is taken as vehicles leading-edge, and kinetic-theory based DSMC method is used to simulate aerothermal environment of hypersonic sphere-cone with different nose radii. Stagnation point heat fluxes calculated by DSMC are compared with that by Fay-Riddell formulae and other theories. Aerothermodynamic characteristics of hypersonic small nose cone with local rarefied gas effect are studied. It is found that the modified Cheng＇s parameter is a credible criterion in predicting rarefied gas effects at stagnation point of sharp leading-edges.
出处
《计算物理》
EI
CSCD
北大核心
2010年第1期59-64,共6页
Chinese Journal of Computational Physics
基金
国家自然科学基金(No.90716011)资助项目
