Results 171 to 180 of about 39,906 (229)
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A review of the shock-dominated flow in a hypersonic inlet/isolator
Progress in Aerospace Sciences, 2023He-xia Huang +11 more
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, 2020
Understanding start–unstart behavior of intakes in hypersonic Mach numbers is essential for seamless operation of scramjet engines.
M. K. Devaraj +4 more
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Understanding start–unstart behavior of intakes in hypersonic Mach numbers is essential for seamless operation of scramjet engines.
M. K. Devaraj +4 more
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Will there or will there not be a hypersonic airplane?
Journal of Engineering Physics and Thermophysics, 2000An analytical overview of the problems of heat transfer occurring in horizontal flight of a body in the earth’s atmosphere at a hypersonic speed is given. It is shown that, despite the enormous experience accumulated in the design and development of shuttle systems (Space Shuttle, Buran), the creation of a hypersonic airplane still remains a serious ...
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Il Nuovo Cimento, 1955
Methods of mixed fields are extended to the case of hyperons. In order to take into account a new particle (Y-particle) which decays into a Λ-particle and a π-meson, a set of the so-called strong interactions between hyperson and mesons is assumed. Then the Λ-particle self-energy is calculated to the second-order terms through the use of the method of ...
H. Enatsu, C. Ihara
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Methods of mixed fields are extended to the case of hyperons. In order to take into account a new particle (Y-particle) which decays into a Λ-particle and a π-meson, a set of the so-called strong interactions between hyperson and mesons is assumed. Then the Λ-particle self-energy is calculated to the second-order terms through the use of the method of ...
H. Enatsu, C. Ihara
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2015
Abstract The chapter starts its analysis with blunt-nosed bodies. In a supersonic flow, a blunt-nosed body produces a bow shock wave. The chapter shows that the shape of the shock and the entire flow between the shock and the body become independent of the Mach number, M∞, provided it is large enough.
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Abstract The chapter starts its analysis with blunt-nosed bodies. In a supersonic flow, a blunt-nosed body produces a bow shock wave. The chapter shows that the shape of the shock and the entire flow between the shock and the body become independent of the Mach number, M∞, provided it is large enough.
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1962
An experimental investigation was made of the flow field behind a two-dimensional circular cylinder at a nominal Mach number of 5.7. The free-stream Reynolds number based on the cylinder diameter was varied over a range from 4300 to 66, 500 by changing both the diameter of the cylinder and the stagnation pressure of the wind tunnel.
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An experimental investigation was made of the flow field behind a two-dimensional circular cylinder at a nominal Mach number of 5.7. The free-stream Reynolds number based on the cylinder diameter was varied over a range from 4300 to 66, 500 by changing both the diameter of the cylinder and the stagnation pressure of the wind tunnel.
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Review of control and guidance technology on hypersonic vehicle
Chinese Journal of Aeronautics, 2022Xiaokui Yue +2 more
exaly
Review of acoustic metasurfaces for hypersonic boundary layer stabilization
Progress in Aerospace Sciences, 2022Juanmian Lei, Rui Zhao, Chihyung Wen
exaly
Proposed for presentation at the Hypersonic Weapons Summit (VIRTUAL) in ,, 2021
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Progress in flight tests of hypersonic boundary layer transition
Acta Mechanica Sinica, 2021Guohua Tu +9 more
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