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Studies on the Effects of Test Gas on the Flow Field around Large Angle Blunt Cone Flying at Hypersonic Mach Number.

机译：超声波马赫数大角度钝锥围绕流域试验气体对流场影响的研究。

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Gopalan Jagadeesh; Kanderpallt Nagashetty; K. P. Jaganntha Reddy; Mingyu Sun; Kazuyoshi Takayama;
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年度 2002
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1. 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
2. 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
3. Studies on the Effects of the Plasma Wake Flow Fields of Hypersonic Reentry Blunt Cone on Electromagnetic Wave [J] . Yuxin Wang, Song Liu, Shuangying Zhong IEEE Transactions on Plasma Science . 2019,第8期

机译：高超声速折返钝角等离子体尾流场对电磁波影响的研究
4. Aerodynamic Drag Reduction Using Aerospikes for Large Angle Blunt Cone Flying at Hypersonic Mach Number [C] . V. Menezes, S. Saravanan, G. Jagadeesh, AIAA Fluid Dynamics Conference and Exhibit . 2002

机译：使用气钉降低空气阻力，以高超声速马赫数飞行大角度钝锥
5. Hypersonic boundary-layer transition measurements at Mach 10 on a large seven-degree cone at angle of attack [D] . Moraru, Ciprian G. 2015

机译：在大七度锥面的迎角处以10马赫的高超声速边界层跃迁测量
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. Hypersonic Laminar Boundary Layer Transition. Part 1. Nosetip Bluntness Effects on Cone Frustum Transition. Part 2. Mach 6 Experiments of Transition on a Cone at Angle of Attack [R] . Stetson, K. F. 1986

机译：高超声速层流边界层转换。第1部分.Nosetip钝性对锥形扭转过渡的影响。第2部分。攻击角度在锥体上过渡的mach 6实验

Studies on the Effects of Test Gas on the Flow Field around Large Angle Blunt Cone Flying at Hypersonic Mach Number.

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