带配平翼钝体高超声速粘性绕流的数值模拟

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，针对配平翼外形给出了贴体性、

The Numerical Simulation of the Hypersonic Viscous Flow over a Blunt Body with Trimming Wings

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.