摘要
采用NND差分格式，通过求解Navier－Stokes方程，数值模拟了带配平翼钝体的高超声速粘性绕流。文中首先以球头驻点压强和热流为参数，讨论了在差分方程左端采用LU－SGS、LU－ADI和对角化ADI三种不同隐式算法收敛效率的异同。然后以带配平翼钝体的高超声速粘性绕流为模型，对所研制的程序进行了计算验证。在计算中采用了代数方法和求解椭圆型方程方法相结合的网格生成技术，针对配平翼外形结出了贴体性、正交性和均匀性较好的计算网格。计算结果分析表明，本文数值计算所得到的气动力及流场结构与相应的实验结果是一致的。
Numerical simulations were made to the hypersonic viscousflow over a blunt body with trimming wings by solving the Navier-Stokesequations with NND finite difference scheme in the present paper.At first, the compariscn was made to the convergence rates of three implicit methods used in,the finite difference method, whieh are LD-SGS,LU-ADI and diagonalized ADI, in the reference of the pressureand the heat transfer rate on the stagnation point of a sphere. Then,the computational verification was made to the computer code to the caseof a hypersonic viscous flow over a blunt body with trimming wings.The grid generation technique with the combination of the algebric andthe elliptic grid generation procedures was used, and the body fitted gridwas generated with good orthogonality and evenness in the configurationwith trimming wings.The analysis to the computational results shows thatthe aerodynatnics and the structure of the flowfield obtained from thenumerical simulation correspond to the experimental results.
出处
《空气动力学学报》
CSCD
北大核心
1997年第4期415-426,共12页
Acta Aerodynamica Sinica
