Previous research studies indicate that the proportion of Magnus force at the spinning projectile tail position is very high. Meanwhile, the large mutations of aerodynamic characteristics are found after adding boattail structures. In order to study the influences of boattail structures on aerodynamics of a spinning projectile, a 6.37-diameter long tangential-ogive-cylinder projectile is selected as the original model. Moreover, several boattail configurations are adopted to investigate the effects of boattail structures on the aerodynamics. Numerical simulations with the use of detached eddy simulation method have been performed to study the modification of boattail structure on the surface pressure of the projectile to expose the effects on the aerodynamic characteristics. The reliability of the numerical method has been validated through comparison with experimental data. The numerical results show that the variations of the wake vortex field due to the boattail structures have important influences on the surface pressure and the aerodynamic characteristics. The results provide important observations which can be valuable for design optimization of supersonic spinning projectile.

中文翻译：

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船尾结构对超音速旋转弹丸气动特性的影响

以往的研究表明，旋转弹尾位置的马格努斯力比例非常高。同时，增加了船尾结构后，空气动力学特性发生了较大的突变。为研究船尾结构对旋转弹丸气动特性的影响，选取直径为6.37的长切向齿形圆柱弹丸作为原始模型。此外，采用几种船尾结构来研究船尾结构对空气动力学的影响。采用分离涡模拟方法进行数值模拟，研究船尾结构对弹丸表面压力的改变，揭示其对气动特性的影响。通过与实验数据的对比，验证了数值方法的可靠性。数值结果表明，船尾结构引起的尾涡场的变化对表面压力和气动特性有重要影响。结果提供了重要的观察结果，对超音速旋转弹丸的设计优化很有价值。