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Exploratory investigation of flow field resulting from forward-facing nozzles exhausting near a large cylindrical body at free-stream Mach numbers of 3.0 and 6.0

机译：对前向喷嘴在自由流马赫数为3.0和6.0时在大圆柱体附近排气产生的流场的探索性研究

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摘要

Flow field from forward facing nozzles exhausting near large cylindrical body at free-stream Mach numbers of 3.0 and 6.0

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作者
Martin, J. A.; Mc Ghee, R. J.;
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年度 1969
页码 1-43
总页数 43
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
CYLINDRICAL BODIES; FLOW DISTRIBUTION; FREE FLOW; HYPERSONIC FLOW; JET NOZZLES; SUPERSONIC FLOW; ANGLE OF ATTACK; BOUNDARY LAYER SEPARATION; JET EXHAUST; MACH NUMBER; STATIC PRESSURE;

机译：圆柱体;流量分配;自由流动;超音速流动; JET NOZZLEs;超音速流;攻击角度;边界层分离; JET EXHaUsT;马赫数;静压力;

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专利

1. EXPERIMENTAL AND NUMERICAL STUDIES ON FLOW FROM AXISYMMETRIC NOZZLE FLOW WITH SUDDEN EXPANSION FOR MACH 3.0 USING CFD [J] . Jaimon D. Quadros, S. A. Khan, A. J. Antony, International Journal of Energy, Environment and Economics . 2016,第1期

机译：CFD 3.0对MACH 3.0轴对称对称喷流突然扩展的实验和数值研究
2. Investigation of Missile-Shaped Body with Forward-Facing Cavity at Mach 8 [J] . Saravanan Selvaraj, Jagadeesh Gopalan, K.P.J. Reddy Journal of Spacecraft and Rockets . 2009,第3期

机译：前进速度为8马赫的导弹形物体的研究
3. Investigation of Missile-Shaped Body with Forward-Facing Cavity at Mach 8 [J] . S. Saravanan, G. Jagadeesh, K. P. J. Reddy Journal of Spacecraft and Rockets . 2009,第3期

机译：前进速度为8马赫的导弹形物体的研究
4. Investigations on effects of free-stream mach numerber on flow and aeroacoustic characteristics in cavity [C] . Yang Dang-guo, Liang Jin-min, Li Jian-qiang, Proceedings of the 2010 Symposium on Piezoelectricity, Acoustic Waves and Device Applications . 2010

机译：自由流马赫数对空腔流动和空气声特性的影响研究
5. MACH REFLECTION, MACH DISC, AND THE ASSOCIATED NOZZLE FREE-JET FLOWS. [D] . CHANG, I-SHIH. 1973

机译：Mach反射，Mach光盘和相关的喷嘴自由流动。
6. Flow visualisation of a normal shock impinging over a rounded contour bump in a Mach 1.3 free-stream [O] . Kin Hing Lo, Konstantinos Kontis -1

机译：撞击在Mach 1.3自由流中的圆形轮廓凸起上的正常冲击的流动可视化
7. Part I. The effect of a simple throat distortion on the downstream flow in a hypersonic wind tunnel nozzle. Part II. An experimental investigation of flow over simple blunt bodies at a nominal Mach number of 5.8 [O] . Oliver Robert E. 1957

机译：第一部分。高超声速风洞喷嘴中简单喉部扭曲对下游流动的影响。第二部分。标称马赫数为5.8的简单钝体流动的实验研究
8. Exploratory Investigation of Flow Field Resulting from Forward-Facing Nozzles Exhausting Near a Large Cylindrical Body at Free-Stream Mach Numbers of 3.0 and 6.0 [R] . Martin, J. A., Mc Ghee, R. J. 1969

机译：自由流马赫数为3.0和6.0的大圆柱体附近前向喷嘴排气流场的探索性研究

Exploratory investigation of flow field resulting from forward-facing nozzles exhausting near a large cylindrical body at free-stream Mach numbers of 3.0 and 6.0

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