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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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Research progress on active thermal protection for hypersonic vehicles
, 2020Zhang Silong +6 more
semanticscholar +1 more source
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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Stabilized methods for high-speed compressible flows: toward hypersonic simulations
Computational Mechanics, 2021D. Codoni +5 more
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Progress in flight tests of hypersonic boundary layer transition
Acta Mechanica Sinica, 2021Guohua Tu +9 more
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Capabilities and limitations of existing hypersonic facilities
, 2020S. Gu, H. Olivier
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