限制器对弹丸阻力计算的影响  

Effect of Limiter on Drag Force Calculation of Bullet

作　　者：周志超[1] 陈新虹[1] 赵润祥[1] 刘松[2] 

机构地区：[1]南京理工大学动力工程学院,南京210094 [2]中国燃气涡轮研究院,成都610500

出　　处：《弹道学报》2010年第2期57-61,共5页Journal of Ballistics

摘　　要：采用通量型NND(无波动无自由参数的耗散)差分格式结合不同限制器,计算了某超音速小攻角飞行弹丸的阻力.给出了沿弹迎/背风面压力系数和切应力系数的分布曲线,分析了不同限制器对阻力系数的影响.结果表明,压缩型限制器捕捉压力和切应力变化的能力最强,耗散型限制器会抹平压力和切应力峰值;耗散型限制器计算的阻力系数误差最大;采用可微限制器计算的层流阻力系数最符合试验值;各限制器计算的摩阻系数随来流马赫数的增大逐步与van Driest工程计算值相吻合.Different kinds of limiters were used in the flux type of NND （non-oscillatory, containing no free parameters and dissipative） scheme, and drag forces of certain kind of bullet with small attack angle were calculated at supersonic. The curves of pressure and tangential stress coefficients along the windward and leeward of the body were given. The effects of different limiters on drag coefficients were analyzed. The result shows that the compressed limiters have the strongest capability of catching the change of pressure and tangential stress, and the dissipative ones can flatten the peak value of stress. The error of the drag coefficient brought by the dissipative limiters is biggest. The drag force of laminar flow computed by differentiable limiters is most accordant to the experiment result. The friction drag coefficients computed by all kinds of limiters become closer to the results of van Driest＇s project method as the coming flow Mach number becoming higher.

关 键 词：弹丸 限制器 NND格式 阻力 

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]