Abstract— The results of the numerical investigation of supersonic flow past a sharp slender body at an angle of attack are given with reference to the example of an axisymmetric cylindrical body with a conical nose. Separated and vortex structures developed at various angles of attack are identified. The effect of anomalous increase in pressure on the leeward side is explained.

中文翻译：

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超音速自由流中攻角轴对称体背风侧涡流结构的发展

摘要：以锥头轴对称圆柱体为例，给出了以攻角通过尖锐细长体的超音速流动的数值研究结果。识别出在不同攻角下形成的分离和涡旋结构。解释了背风侧压力异常增加的影响。