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A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack

机译：一种在零迎角下预测各种钝体的冲击形状和压力分布的方法

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摘要

Relationship of shock standoff distance, at sonic and stagnation points, to body geometry of blunt bodies at zero angle of attack

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作者
Kaattari, G. E.;
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年度 1968
页码 1-41
总页数 41
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
BLUNT BODIES; BOW WAVES; SHOCK WAVES; ATMOSPHERIC ENTRY; CORRELATION COEFFICIENTS; FLOW GEOMETRY; PRESSURE DISTRIBUTION; REENTRY PHYSICS; SHOCK WAVE PROPAGATION; STAGNATION POINT; SUBSONIC FLOW;

机译：BLUNT BODIEs;弓波;冲击波;大气入口;相关系数;流动几何;压力分布; REENTRY pHYsICs;冲击波传播; sTaGNaTION pOINT; sUBsONIC FLOW;

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专利

1. Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle of attack [J] . SU Cai-hong, ZHOU Heng 应用数学和力学（英文版） . 2007,第005期

机译：零迎角小鼻钝的钝锥上高超声速边界层的稳定性分析和过渡预测
2. Effects of Angle of Attack and Bluntness on Heating Rate Distribution of Blunt Models at Hypersonic Speeds [J] . Fluid Dynamics . 2019,第6期

机译：攻击角度与钝化对高音速度钝化模型加热速率分布的影响
3. Heat reduction mechanism of hypersonic spiked blunt body with installation angle at large angle of attack [J] . Huang Jie, Yao Wei-Xing, Qin Ning Acta astronautica . 2019,第Nova期

机译：大迎角安装角下高超声速尖刺钝体的降温机理
4. Numerical Computation of Pressure Distributions over Conical Forebody at High Angles of Attack [C] . Yu Yang, Borui Zheng, Wei Yang, AIAA aerospace sciences meeting including the new horizons forum and aerospace exposition . 2012

机译：大迎角下锥形前体压力分布的数值计算
5. Effects of nose bluntness and shock-shock interactions on blunt bodies in viscous hypersonic flows. [D] . Singh, Dal Jeet. 1989

机译：鼻子过钝和电击-相互作用对粘性高超声速流动中钝体的影响。
6. Predictors of Intraocular Pressure After Phacoemulsification in Primary Open-Angle Glaucoma Eyes with Wide Versus Narrower Angles (An American Ophthalmological Society Thesis) [O] . Shan C. Lin, Marisse Masis, Travis C. Porco, 2017

机译：开眼角膜青光眼在较宽和较窄角度的超声乳化后眼内压的预测指标（美国眼科学会论文）
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. A Method for Predicting Shock Shapes and Pressure Distributions for a Wide Variety of Blunt Bodies at Zero Angle of Attack [R] . Kaattari, G. E. 1968

机译：一种预测零角度下各种钝体的冲击形状和压力分布的方法

A method for predicting shock shapes and pressure distributions for a wide variety of blunt bodies at zero angle of attack

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