摘要
三维流场的数值模拟是国外军事技术发达国家在飞行器设计过程中所采用的重要方法。本文建立了导弹的真实三维几何外形,然后结合实验数据,采用有限体积法,对国产某典型反舰导弹在高亚音速、不同攻角时的三维流场进行了数值模拟。计算出了导弹在不同工况下的阻力系数、升力系数和力矩系数。把计算所得结果与实验值进行了比较,用理论公式对计算结果进行了对比分析,并简单地分析了偏差的原因和解决的可行措施。文中所用的残差光顺技术和网格自适应技术能有效地提高计算的收敛速度和精度。
Based on experimental data, adopting a finite volume method, a numerical simulation method is applied to the three -dimensional flow field about the air- to- surface missiles at high subsonic speed and during the different angle of attack. The drag coefficient, lift coefficient and force moment coefficient under the different operating mode of missiles are calculated in the paper. Calculation resuhs and the experiment data are, compared, the results with theory formula are analyzed, the reasons of difference between them are analyzed simply, and some feasible measures are, offered.
出处
《航空计算技术》
2006年第5期76-79,共4页
Aeronautical Computing Technique
关键词
导弹
三维流场
数值模拟
气动力系数
missile
three-dimensional flow field
numerical simulation
aero dynamical coefficient
