Zobrazeno 1 - 10
of 21
pro vyhledávání: '"T. Nilavarasan"'
Publikováno v:
European Journal of Mechanics - B/Fluids. 99:98-115
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::40949204409e26277fa5c01b0edd4d04
https://doi.org/10.1016/j.euromechflu.2023.01.007
https://doi.org/10.1016/j.euromechflu.2023.01.007
Publikováno v:
European Journal of Mechanics - B/Fluids. 95:160-177
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::723a5c645574de2a30c441e30a12bad1
https://doi.org/10.1016/j.euromechflu.2022.04.010
https://doi.org/10.1016/j.euromechflu.2022.04.010
Autor:
T. Nilavarasan, Ganapati N. Joshi
Publikováno v:
Lecture Notes in Mechanical Engineering ISBN: 9789811969690
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::ab24b646b82de2edfb48800415d592eb
https://doi.org/10.1007/978-981-19-6970-6_78
https://doi.org/10.1007/978-981-19-6970-6_78
Publikováno v:
Journal of Visualization. 24:991-1010
Effect of ′ramped vane′-type vortex generators on a shock-induced flow separation in the vicinity of an axisymmetric compression corner was evaluated. Numerical simulations were performed at Mach 2 on a cone–cylinder–flare model with a flare
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::19044b3a4ba3d1a6e7700f3b835deb16
https://doi.org/10.1007/s12650-020-00735-x
https://doi.org/10.1007/s12650-020-00735-x
Akademický článek
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Publikováno v:
The Aeronautical Journal. 124:121-149
The ability of microramps to control shock - boundary layer interaction at the vicinity of an axisymmetric compression corner was investigated computationally in a Mach 4 flow. A cylinder/flare model with a flare angle of 25° was chosen for this stu
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::46441f1d7ee5b7bd2429fad908a2dcb8
https://doi.org/10.1017/aer.2019.138
https://doi.org/10.1017/aer.2019.138
Publikováno v:
International Journal of Turbo & Jet-Engines. 39:343-355
Two dimensional computations were conducted to investigate the performance of NACA 0010 cascades with Gurney Flaps. The cascades with three different stagger angles (βB) viz. 45°, 90° and 135° were studied for the aerodynamic performance characte
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::a8eab829c5bdfcdbc4087186a440f021
https://doi.org/10.1515/tjj-2019-0013
https://doi.org/10.1515/tjj-2019-0013
Publikováno v:
International Journal of Turbo & Jet-Engines. 38:263-272
Computational investigations on the effect of Gurney flaps in a NACA 0010 cascade with a 90oblade angle were carried out using STARCCM+ code. The flaps were positioned at the trailing edge of the blades and were aligned at 45oand 90oto the blade chor
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::35c865422756eb85688aebd97626aa28
https://doi.org/10.1515/tjj-2018-0012
https://doi.org/10.1515/tjj-2018-0012
Akademický článek
Tento výsledek nelze pro nepřihlášené uživatele zobrazit.
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Publikováno v:
Proceedings of the 32nd International Symposium on Shock Waves (ISSW32 2019).
Externí odkaz:
https://explore.openaire.eu/search/publication?articleId=doi_________::08b95f853f6694438f80afd858fb8187
https://doi.org/10.3850/978-981-11-2730-4_0094-cd
https://doi.org/10.3850/978-981-11-2730-4_0094-cd