摘要
针对再入飞行器激波层辐射加热,应用有限体积法计算辐射传输方程,引入了一种边界处理方式——虚网格方法,根据化学非平衡流场数据,计算出飞行器表面辐射加热热流。通过分析发现:采用虚网格方法处理辐射传输边界,能够确保真正的边界条件得到应用,满足真实的物理意义,且辐射传输计算的空间网格、立体角网格、初始温度值的收敛性很好,计算结果精度误差小于2.5%。利用虚网格方法计算飞船再入返回时的辐射加热,结果表明计算所得壁面辐射热流与其他研究者辐射热流计算结果符合良好。
Targeting the shock layer radiation heating,the radiative transfer equation was calculated by finite volume method,in which a way of boundary treatment,called as ghost cell method,was introduced.Based on the chemical non-equilibrium flow field data,radiation heat flux at wall was computed.The analysis reveals that ghost cell method in dealing with radiative transfer boundary ensures that the boundary conditions fit the physical fact.Good convergence and accuracy within 2.5% have been achieved,validating the physical model and numerical methods.Radiation heating computation of spacecraft using ghost cell method shows that computational radiative heating results agree well with the other researchers＇ computational results.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2017年第8期1827-1834,共8页
Journal of Aerospace Power
基金
国家自然科学基金(11402251)
关键词
高超声速
再入
辐射加热
虚网格
辐射传输方程
有限体积法
hypersonic
re-entry
radiant heating
ghost cell
radiative transfer equation
finite volume method
