摘要
将ＳＬＩＰ格式和ＬＵ－ＳＳＯＲ隐式迭代方法结合，数值模拟了尖头母弹在开舱前后的跨声速定常流场。采用修正的Ｂ－Ｌ湍流模型，用轴对称Ｎ－Ｓ方程求解零攻角时母弹在Ｍａｃｈ数０．９４～０．９８ 的临界气动特性和空腔流特性。开舱前母弹计算结果与实验以及Ｓａｈｕ 的结果能够很好吻合， 开舱后空腔流的计算结果也给出了合理的理论分析。
The combination of SLIP scheme and LU SSOR method is used to predict the steady state aerodynamics of trans sonic ogive dispenser at Mach number 0.94 to 0.98; and the modified B L turbulence model is applied in solving axisymmetric Navier Stokes equation. Computed surface pressures of dispenser without cave have been compared with experiments as well as Sahu's numerical results and are found to be in good agreement; The results of cavity flow are also found to be reasonable.
出处
《国防科技大学学报》
EI
CAS
CSCD
1999年第6期32-36,共5页
Journal of National University of Defense Technology
