Zobrazeno 1 - 10
of 10
pro vyhledávání: '"Lian-jie Yue"'
Publikováno v:
AIAA Journal. 61:555-572
The prediction of unstart boundaries of hypersonic inlets is significant to the engine control. To correct the previous conclusions based on the one-dimensional and inviscid flow assumption, the present paper numerically investigates the unstart char
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::71b5331103c9c545eb458c91bcaa89c6
https://doi.org/10.2514/1.j061874
https://doi.org/10.2514/1.j061874
Publikováno v:
AIAA Journal. 60:4462-4466
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::1180d22d0db028e6bbcf5a3304da1978
https://doi.org/10.2514/1.j061392
https://doi.org/10.2514/1.j061392
Publikováno v:
AIAA Journal. Oct2023, Vol. 61 Issue 10, p4230-4046. 17p.
Publikováno v:
Physics of Fluids. 34:071703
Separation-induced shock reflections in straight ducts are generally considered asymmetric for Mach numbers beyond 2.2, but our experiment shows that this is not always the case. A symmetric shock pattern, a proven outcome of following the free-inter
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::ac256d0260fa4b767332ea0a4e9cb881
https://doi.org/10.1063/5.0101760
https://doi.org/10.1063/5.0101760
Publikováno v:
Physics of Fluids. 34:066106
Shock-train transitions in simplified curved isolators are carefully studied by simulation. The results show the shock-train behavior is subject to the complex pressure field created by the duct deflection, eventually presenting five modes during a b
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::e83027d5c979ce8109fcd6127075b476
https://doi.org/10.1063/5.0095277
https://doi.org/10.1063/5.0095277
Publikováno v:
Combustion Science and Technology. 179:2199-2217
Supersonic combustion of thermally cracked kerosene was experimentally investigated in two model supersonic combustors with different entry cross-section areas. Effects of entry static pressure, entry Mach number, combustor entry geometry, and inject
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::204bd63e2b1ee39b461f9e9da91a5b1d
https://doi.org/10.1080/00102200701386198
https://doi.org/10.1080/00102200701386198
Publikováno v:
Proceedings of the Combustion Institute. 30:2859-2866
Investigation of kerosene combustion in a Mach 2.5 flow was carried out using a model supersonic combustor with cross-section area of 51 mm × 70 mm and different integrated fuel injector/flameholder cavity modules. Experiments with pure liquid atomi
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::58057726c0de0f43ecbb1152cce20034
https://doi.org/10.1016/j.proci.2004.07.050
https://doi.org/10.1016/j.proci.2004.07.050
Publikováno v:
42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
Supersonic combustion of supercritical/cracked kerosene was experimentally investigated in two supersonic model combustors with different entry cross section areas. The flow rate and composition of supercritical/cracked kerosene were characterized. U
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::b4d95397f87acb44fdfdea0788402adc
https://doi.org/10.2514/6.2006-4514
https://doi.org/10.2514/6.2006-4514
Publikováno v:
41st AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit.
Supersonic combustion characteristics of partially-cracked kerosene were experimentally investigated. The experiments were conducted in a Mach 3.0 supersonic model combustor with a cross-section of 70 mm in height and 51 mm in width. A two-stage kero
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::0d526e0cf8d2c3d85503edd78a350467
https://doi.org/10.2514/6.2005-3714
https://doi.org/10.2514/6.2005-3714
Publikováno v:
AIAA Journal. Mar2022, Vol. 60 Issue 3, p1978-1982. 5p.