Zobrazeno 1 - 10
of 13
pro vyhledávání: '"Dundian GANG"'
Publikováno v:
Chinese Journal of Aeronautics. 35:89-101
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::b4588b2cc9e03d38de762765f6ca1348
https://doi.org/10.1016/j.cja.2022.04.014
https://doi.org/10.1016/j.cja.2022.04.014
Publikováno v:
Journal of Thermophysics and Heat Transfer. 36:296-302
An experimental study on the effects of Backward-Facing Step (BFS) shapes was conducted in the Ma6 hypersonic wind tunnel. The step shape was changed by installing different ramps in the step corne...
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::d9e02c5acebd60a78c511310eca1d051
https://doi.org/10.2514/1.t6327
https://doi.org/10.2514/1.t6327
Publikováno v:
Chinese Journal of Aeronautics. 35:90-97
An experimental study was conducted on turbulent separation behaviors induced by blunt fins with different sweep angles at Mach number 6.0. The Nano-particle based Planar Laser Scattering technique (NPLS) was applied to visualize the flowfield, compl
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::8a2e2bde28718514ff220042f19edfaa
https://doi.org/10.1016/j.cja.2021.03.032
https://doi.org/10.1016/j.cja.2021.03.032
Investigation on Heat Transfer Characteristics over Hypersonic Backward-Facing Step of a Blunt Plate
Publikováno v:
Fluid Dynamics. 56:754-763
The combined effect of leading-edge bluntness and backward-facing step (BFS) is critical because they affect the surface thermal loads and boundary layer transition of hypersonic vehicles, which involves engine design, passive thermal protection and
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e4021fa100f43853a30543eee1aaf837
https://doi.org/10.1134/s0015462821050104
https://doi.org/10.1134/s0015462821050104
Publikováno v:
Journal of Visualization. 24:1123-1130
The experimental study of supersonic flow over a spherically blunt cylinder with a spin rate of 600 rpm is reported concerning the characteristics of the vortex structures. Experiments are conducted in a Mach 3.0 wind tunnel, and the nano-tracer plan
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::76a9943b05cbe4645780029fc3308dd8
https://doi.org/10.1007/s12650-021-00762-2
https://doi.org/10.1007/s12650-021-00762-2
Publikováno v:
Journal of Visualization. 24:461-470
The unsteady flow structures and pressure fluctuations of the cylinder-induced shock wave/boundary layer interactions (SBLIs) were investigated at Mach 3.4 and 3.8. The cylinders were mounted on the test section floor with a turbulent boundary layer,
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1aa8a76264135a7c6b27964abf938943
https://doi.org/10.1007/s12650-020-00723-1
https://doi.org/10.1007/s12650-020-00723-1
Publikováno v:
Fluid Dynamics. 55:566-577
In this paper, the experimental study on the shock wave and turbulent boundary layer interactions was performed in the Mach 3.4 supersonic low-noise wind tunnel. The angle of the shock generator was θ = 15°, and the unit Reynolds number of 6.30 ×
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1c3bdee1a126b89c72f79626640494c0
https://doi.org/10.1134/s0015462820030088
https://doi.org/10.1134/s0015462820030088
Publikováno v:
Journal of Visualization. 19:581-585
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0a00596e9dd5d5ad4edda7f38dca98d8
https://doi.org/10.1007/s12650-016-0354-x
https://doi.org/10.1007/s12650-016-0354-x
Publikováno v:
Acta Astronautica. 118:199-209
The effect of surface roughness on boundary layer transition is of great importance to hypersonic vehicles. In this paper, both experimental and numerical methods are used to investigate the laminar-turbulent transition of a Mach 3 flat-plate boundar
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::2e679395c7a6018849169d250e27a86e
https://doi.org/10.1016/j.actaastro.2015.10.008
https://doi.org/10.1016/j.actaastro.2015.10.008
Publikováno v:
SCIENTIA SINICA Physica, Mechanica & Astronomica. 50:104706
In this paper, the interactions between shock wave and the turbulent boundary layer of an incoming wall were experimentally studied. The experiments were performed in a Mach 3.4 supersonic low-noise wind tunnel at the unit Reynolds number of 6.30×10
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::c01a7b687bd732aed9c5f832444bd46b
https://doi.org/10.1360/sspma-2020-0055
https://doi.org/10.1360/sspma-2020-0055