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基于(剪切应力输运)SST湍流模型和尺度自适应模拟方法(SST-SAS)分别对M910旋转稳定弹丸不同马赫数、不同转速情况下的气动参数及流场特性进行数值计算,并对流场结构进行机理性分析。计算结果表明,基于SST湍流模型的定常CFD数值模拟方法可以较好的计算阻力、法向力、俯仰力矩和压心系数,不能准确预测亚音速和跨音速阶段旋转弹丸的滚转阻尼系数以及马格努斯力矩系数导数。采用非定常的尺度自适应模拟方法可以较好的计算旋转弹丸亚音速到超高音速阶段的滚转阻尼系数和马格努斯力矩系数导数。能否准确捕捉非定常尾涡效应对亚音速和跨音速段滚转阻尼及马格努斯力矩计算精度影响很大。采用“全隐式多网格完全耦合求解技术”具有计算速度快、数值稳定的优点。同时,编写的批文件计算脚本提高了计算效率。
Based on the SST turbulence model and SST-SAS, the aerodynamic parameters and flow field characteristics of M910 rotating stable projectile at different Mach numbers and different rotational speeds are calculated respectively, Field structure of a mechanistic analysis. The results show that the steady-state CFD numerical simulation method based on SST turbulence model can well calculate the drag, normal force, pitch moment and pressure coefficient, and can not accurately predict the roll damping coefficient of the projectile and transonic rotation projectile. Guinness moment coefficient derivative. The unsteady scale adaptive simulation method can be used to calculate the roll damping coefficient and the Magnus moment coefficient derivative of the projectile subsonic to the ultra-high velocity stage. The ability of accurately capturing unsteady wake effects greatly affects the roll damping and the Magnus moment calculation accuracy in subsonic and transonic sections. Adopting “all implicit multi-grid complete coupling solution technology” has the advantages of fast calculation speed and stable numerical value. At the same time, the preparation of batch file calculation script to improve the computational efficiency.