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An experimental investigation by hypersonic flow over blunt nosed cones at a mach number of 5.8.

机译：高超声速流过钝头锥的马赫数为5.8的实验研究。

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http://www.archive.org/details/experimentalinve00mach

机译：HTTP://呜呜呜.archive.org/details/experimental in VE00马超

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作者
Machell Reginald M.;
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年度 1956
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正文语种 en_US
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1. 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
2. Experimental study of the influence of small angles of attack and cone nose bluntness on the stabilization of hypersonic boundary layer with passive porous coating [J] . S.O. Morozov, S.V. Lukashevich, V.G. Soudakov, Thermophysics and Aeromechanics . 2018,第6期

机译：攻击小角度钝化对具有无源多孔涂层稳定性边界层稳定的实验研究
3. Numerical Investigation of a Spiked Blunt Nose Cone at Hypersonic Speeds [J] . M. Gauer, A. Paull Journal of Spacecraft and Rockets . 2008,第3期

机译：高超声速尖刺钝锥锥体的数值研究
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. 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. 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 of hypersonic flow over blunt nosed cones at a Mach number of 5.8. [O] . OBryant William T. 1956

机译：马氏数为5.8的钝鼻锥上高超音速流动的实验研究。

An experimental investigation by hypersonic flow over blunt nosed cones at a mach number of 5.8.

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