MATEC Web Conf.
Volume 115, 2017XXXIII Siberian Thermophysical Seminar (STS-33)
|Number of page(s)||4|
|Section||Chapter 3 Transport processes in physical and chemical transitions, including combustion|
|Published online||10 July 2017|
Numerical and experimental study of supersonic combustion chamber at entrance Mach number 4. Part 1: Non-reacting flow
ITAM SD RAS, 4/1 Institutskaya Str., Novosibirsk, 630090, Russia
* Corresponding author: email@example.com
Results of joint experimental and numerical study are presented for a non-reacting 3D flow in a channel with backward-facing steps (BFS) located on top and bottom walls. Experiments were conducted in a hot-short wind tunnel at entrance Mach number 4, total pressure 9.5 bar and total temperature 2120K. Argon was injected into the channel from eight round holes, placed on channel walls upstream of the channel expansion. Simulations performed in a 3D RANS approach with k-ω SST turbulence model give a reasonable agreement with experimental data and allow evaluating the pressure flowfield and argon mass concentration in the channel.
© The Authors, published by EDP Sciences, 2017
This is an Open Access article distributed under the terms of the Creative Commons Attribution License 4.0, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
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