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Newtonian Aerodynamics for Circular Cones Modified to Produce Lift at Zero Angle of Attack

机译：改进的圆弧锥体在零攻角下产生升力的牛顿空气动力学

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作者
Short, B. J.;
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年度 1969
页码 1-3
总页数 3
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Circular cones ; Lift drag ratio ; Newton theory ; Zero angle of attack ; Aerodynamic configurations ; Aerodynamic stability ; Graphs (charts) ; Reentry vehicles ; Supersonic flow;

机译：圆锥;升阻比;牛顿理论;零攻角;气动配置;气动稳定性;图（图）;再入飞行器;超音速流;

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1. Experimental study on aerodynamic noise generated from two-dimensional models (2nd report, effect of the angle of inclination of circular cylinders and the angle of attack of square cylinders to aerodynamic noise) [J] . Shoji Yamada, Hajime Fujita, Yosiyuki Maruta 日本機械学会論文集. B編 . 1997,第610期

机译：二维模型产生的空气动力噪声的实验研究（第二次报告，圆柱倾斜角和方形圆柱的迎角对空气动力噪声的影响）
2. Effect of thermochemical non-equilibrium on the aerodynamics of an osculating-cone waverider under different angles of attack [J] . Liu Zhen, Liu Jun, Ding Feng, Acta astronautica . 2017,第octa期

机译：在不同迎角条件下，热化学非平衡对振动锥波导管的空气动力学的影响
3. Experimental and analytical analysis of aerodynamic lift of an ornithopter at low and high angles of attack [J] . Bakhtiari Abdolbaghi, Haghighi Shahram Ehtemadi, Maghsoudpour Adel Proceedings of the Institution of Mechanical Engineers . 2019,第6期

机译：飞机在低和高攻角下的气动升力的实验和分析分析
4. Aerodynamic and Aeroacoustic Analysis of SCCH Models of Four High-Lift Configurations near the Stall Angle of Attack [C] . Xuyang Ma, Yuejun Shi, Wenbin Song AIAA AViation Forum . 2020

机译：空气动力学和空气声学分析SCCH型号的四个高升力配置附近的攻击角度
5. Hypersonic crossflow instability and transition on a circular cone at angle of attack. [D] . Ward, Christopher A. C. 2010

机译：高音速横流失稳和在迎角处的圆锥上过渡。
6. Monte Carlo calculation of photo-neutron dose produced by circular cones at 18 MV photon beams [O] . Elham Hosseinzadeh, Nooshin Banaee, Hassan Ali Nedaie 2018

机译：蒙特卡洛计算圆锥在18MV光子束下产生的光中子剂量
7. Measurements of the pressure distributions on two circular cylinders of diameter d, vertically immersed in a turbulent boundary layer, are performed for various cylinder spacings s and angles of attack φ. The characteristics of the drag and lift forces acting on the cylinder are classified into three regions : i.e., 1) 0°＜__〜φ＜__〜30°, 2) 30°＜__〜φ＜__〜120°and 3) 120°＜__〜φ＜__〜180°which are divided by the two zero-lift force lines. Moreover, it is found that the interference between two cylinders is almost negligible for s/d＞__〜4, except for the influence of the wake region of the upstream cylinder. [O] . 谷口清一, 坂本弘志, Seiichi TANIGUCHI, 1980

机译：对于不同的气缸间距s和迎角φ，对垂直浸入湍流边界层的直径为d的两个圆柱上的压力分布进行测量。作用在气缸上的阻力和提升力的特性分为三个区域：1）0°＜__ 〜φ ＜__ 〜30°，2）30°＜__ 〜φ ＜__ 〜120°和3） 120°＜__ 〜φ ＜__ 〜180°除以两条零升力线。而且，发现除了上游气缸的尾流区域的影响之外，对于s / d＞ __〜4，两个气缸之间的干扰几乎可以忽略。
8. Newtonian aerodynamics for circular cones modified to produce lift at zero angle of attack [R] . Short, B. J. 1969

机译：圆锥体的牛顿空气动力学被修改为在零迎角时产生升力

Newtonian Aerodynamics for Circular Cones Modified to Produce Lift at Zero Angle of Attack

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