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数值模拟了不同马赫数,不同喷流压比下的轴对称超声速底部喷流干扰流场,采用LU隐式算法进行数值求解并引入了Baldwin-Lomax代数湍流模型。采用分区网格将弹身与底部区域合为一个整体进行计算,得到了清晰的流场结构和弹体表面及底部的压力分布,并与试验结果进行了比较。数值模拟结果表明超声速底部喷流干扰流场结构复杂,有、无喷流时底部流场有很大不同,喷流对底压分布有明显影响,进而对轴向力系数影响显著。
Numerical simulations of axial flow at supersymmetric supersonic bottom jet with different Mach numbers and different jet pressure ratios were carried out. The LU implicit algorithm was used to solve the problem numerically and Baldwin-Lomax algebraic turbulence model was introduced. The partition grid is used to calculate the elastic body and the bottom area as a whole, and a clear flow field structure and the pressure distribution on the surface and bottom of the projectile are obtained and compared with the experimental results. The results of numerical simulation show that the supersonic jet flow at the bottom of the supersonic jet has a complex flow field structure. The flow field at the bottom and bottom of the supersonic jet flow is very different. The jet flow has a significant effect on the pressure distribution and has a significant effect on the axial force coefficient.