Zobrazeno 1 - 10
of 29
pro vyhledávání: '"Igor Klioutchnikov"'
Publikováno v:
Journal of fluid mechanics 957, A8 (2023). doi:10.1017/jfm.2023.56
Journal of fluid mechanics 957, A8 (2023). doi:10.1017/jfm.2023.56
Published by Cambridge Univ. Press, Cambridge [u.a.]
Published by Cambridge Univ. Press, Cambridge [u.a.]
Publikováno v:
Proceedings of the Combustion Institute.
Publikováno v:
AIAA Journal. 58:3706-3710
Publikováno v:
AIAA Journal. 57:3874-3884
Direct numerical simulation of Gortler vortices in hypersonic compression ramp flow is performed. Three ramp angles of 15, 20, and 25 deg are considered for a freestream Mach number of 7.7 and a un...
Numerical study of chemically reacting flow in a shock tube using a high-order point-implicit scheme
Publikováno v:
Computers & Fluids. 184:107-118
The shock wave/boundary-layer interaction of chemically reacting flow in a shock tube is studied using a high-order point-implicit solver. The solver employs a high-resolution weighted essentially non-oscillatory (WENO) scheme to capture the complex
Autor:
Igor Klioutchnikov, Oleg Kliuchnikov
Publikováno v:
IV International Scientific and Practical Conference.
Publikováno v:
Journal of Fluid Mechanics. 912
Direct numerical simulations (DNS) are performed to investigate a hypersonic flow over a compression ramp with a free stream Mach number of 7.7 and a free stream Reynolds number of based on the flat plate length. The DNS results are validated by comp
Autor:
Shibin Cao, Herbert Olivier, Chih-yung Wen, Karl Alexander Heufer, Jiaao Hao, Igor Klioutchnikov
Publikováno v:
Journal of fluid mechanics 923, A27 (2021). doi:10.1017/jfm.2021.552
Journal of fluid mechanics 923, A27 (2021). doi:10.1017/jfm.2021.552
Published by Cambridge Univ. Press, Cambridge [u.a.]
Published by Cambridge Univ. Press, Cambridge [u.a.]
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_dedup___::0ffc4027a40334b0b6c23cc9afbb9283
Publikováno v:
Aerospace Science and Technology. 81:65-77
In transonic airfoil flow, pressure waves are generated mainly at the trailing edge and in the case of a shock in the region of the shock/boundary layer interaction. Depending on the Mach number, these waves lead to oscillating shock waves and an uns
Autor:
Igor Klioutchnikov
Publikováno v:
6th SGEM International Multidisciplinary Scientific Conferences on SOCIAL SCIENCES and ARTS Proceedings, Modern Science.