弹丸旋转空气动力效应非定常数值模拟  

Unsteady numerical simulation of aerodynamic effect of a spinning projectile

作　　者：刘周[1] 谢立军[1] 杨云军[1] 周伟江[1] 

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《航空学报》2016年第5期1401-1410,共10页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(11372040;11472258)~~

摘　　要：准确计算马格努斯力和力矩对旋转弹箭设计、弹道计算和稳定性研究都至关重要。采用非定常雷诺平均Navier-Stokes(RANS)方程对高速旋转的SOCBT弹丸进行了数值模拟,纵向气动特性在整个攻角范围内都较好地与试验值保持一致,而侧向气动特性马格努斯力和力矩在小攻角范围与试验数据吻合较好,在大攻角范围却存在一定的差异。采用延迟分离涡模拟(DDES)方法的计算结果有较为明显的改善,对比研究表明分离点位置对马格努斯效应有着显著影响。表明DDES方法对于提高旋转弹箭马格努斯效应的数值模拟精度有较大的潜力。The accurate calculation of Magnus force and moment is essential to the design,trajectory calculations and stability analysis of rotation missiles.The unsteady Reynolds averaged Navier-Stokes（RANS）method is taken to simulate the flow over the high-speed spinning projectile SOCBT.The longitudinal aerodynamic characteristics over the entire range of angles of attack are consistent with the experimental data,while the lateral aerodynamic characteristics,including Magnus force and moment,in a small angle of attack range are in good agreement with the experimental data,but the deviation is evident in the range of high angles of attack.The adoption of the delay detached eddy simulation（DDES）method has a significant improvement in the range of high angles of attack,and comparative studies have shown that the separation point has a significant influence on Magnus effect.The results show that the DDES method has great potential for improving the simulation accuracy of Magnus effect of the spinning missiles.

关 键 词：旋转 弹丸 马格努斯效应 延迟分离涡模拟 SCOBT 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]