摘要
由于过渡区域流动的物理现象的复杂性和流动控制方程的非线性,航天飞行器设计所需要的气动加热特性目前主要由工程计算方法得到.为了使计算过渡流区热流的Linear桥函数方法能适用于广泛应用的钝锥体外形,拟合得到了相应的调节参数,使用DSMC方法对计算结果进行验证.验证结果表明该调节参数适用于钝锥体外形,使得Linear桥函数在过渡流区能比较准确地计算钝锥体物面热流.
Due to the complex flow in the transitional regime and the nonlinearity of the flow control functions,when a launch verhicle is designed,the aerodynamic heating is predicted mainly by engineering method.The accommodation parameter of linear bridging relation which is used to calculate the heat flux in transitional regime is fixed to fit the blunt cone which is widely used.The results of the bridging relation are validated by using the DSMC method.The validation shows that the accommodation parameter suited for the blunt cone and ensuring the linear bridging relation may be used to calculate the heat flux of blunt cone in a transitional regime.
出处
《物理学报》
SCIE
EI
CAS
CSCD
北大核心
2012年第4期51-55,共5页
Acta Physica Sinica
基金
高校博士点专项科研基金(批准号:200899980006)
国家自然科学基金重点研究项目(批准号:90916018)
湖南省自然科学基金(批准号:09JJ3109)资助的课题~~
关键词
过渡流区钝锥体
桥函数
DSMC方法
调节参数
blunt cone in transitional regime
bridging relation
DSMC method
accommodation parameter
