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An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic mach numbers

机译：高超音速马赫数下钝锥的压力分布和流场的实验和理论研究

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Pressure distribution and flow fields of blunted cones at hypersonic Mach numbers

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作者
Cleary, J. W.;
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年度 1965
页码 1-77
总页数 77
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
BLUNT BODIES; FLOW DISTRIBUTION; HYPERSONIC SPEED; HYPERSONICS; MACH NUMBER; PRESSURE DISTRIBUTION; BLUNT BODY; FLOW FIELD; HYPERSONIC SPEED; MACH NUMBER; PRESSURE DISTRIBUTION;

机译：BLUNT BODIEs;流量分配;超速的;高超声速;马赫数;压力分布; BLUNT BODY;流场;超速的;马赫数;压力分布;

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专利

1. Flow Fields of a Large-Angle, Spiked Blunt Cone at Hypersonic Mach Numbers [J] . Jagadeesh GOPALAN, Viren MENEZES, K.P. Jagannatha REDDY, Transactions of the Japan society for aeronautical and space sciences . 2005,第160期

机译：高超声速马赫数的大角度尖刺钝锥的流场
2. Studies on the Effects of Test Gas on the Flow Field around Large Angle Blunt Cone Flying at Hypersonic Mach Number [J] . Gopalan JAGADEESH, Kanderpallt NAGASHETTY, K. P. Jaganntha REDDY, Transactions of the Japan society for aeronautical and space sciences . 2002,第149期

机译：试验气体对高超声速马赫数大角钝锥飞行流场的影响研究
3. Experimental investigation of nose-tip bluntness effects on the hypersonic crossflow instability over a cone [J] . Niu Haibo, Yi Shihe, Liu Xiaolin, International Journal of Heat and Fluid Flow . 2020,第Deca期

机译：鼻尖钝性效应对锥体超声交叉流动性的实验研究
4. Numerical Investigation of Hypersonic Flow Past a Spherically Blunted Nose Cone [C] . Ashish Narayan, Rakesh Kumar, S. Narayanan International Conference on Application of Fluid Dynamics . 2018

机译：超声波流过球形叶片的数值调查
5. THEORETICAL AND EXPERIMENTAL INVESTIGATION OF HYPERSONIC VISCOUS SHOCK LAYER ON A BLUNT-NOSED BODY. [D] . KRISHNARAO, DANDAMUDI V. 1972

机译：钝头体上的超音速粘性冲击层的理论和实验研究。
6. Effect of a Roughness Element on the Receptivity of a Hypersonic Boundary Layer over a Blunt Cone Due to Pulse Entropy Disturbance with a Single Frequency [O] . Zhenqing Wang, Mingfang Shi, Xiaojun Tang, 2018

机译：粗糙元件对钝锥体上超声边界层的接受性的影响由于单频脉冲熵干扰
7. An experimental investigation by hypersonic flow over blunt nosed cones at a mach number of 5.8. [O] . Machell Reginald M. 1956

机译：高超声速流过钝头锥的马赫数为5.8的实验研究。
8. An Experimental and Theoretical Investigation of the Pressure Distribution and Flow Fields of Blunted Cones at Hypersonic Mach Numbers [R] . Cleary, J. W. 1965

机译：高超声速马赫数下钝锥压力分布和流场的实验与理论研究

An experimental and theoretical investigation of the pressure distribution and flow fields of blunted cones at hypersonic mach numbers

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