Numerical simulation on supersonic shock wave/turbulent boundary interaction

DOI

10.2991/ifmca-16.2017.136How to use a DOI?

Keywords

turbulence model; numerical simulation; supersonic; shock wave; turbulence; heat transfer

Abstract

Supersonic shock wave/turbulent boundary layer interactions were simulated by employing three popular engineering turbulence models, namely Spalart-Allmaras(SA), k- , shear stress transport(SST) over a 24ºcompression ramp at Mach 2.84 and a 11º×11º double-sharp fin plates at Mach 2.91. Comparisons of pressure distributions and skin friction coefficient on the wall with experimental results show that, for the compression ramp, SA model is superior to other models for calculating pressure distribution, the friction coefficient given by SST model is closest to the experimental results. For double fin plates, the pressure distributions of three turbulence models are all close to the experimental results at the centerline, except peaking value, SST model is more accurate for skin friction distributions than SA model and K- model. In summary, SST model is more accurate for calculating wall pressure and skin friction coefficient distributions, improvements must be made for simulating supersonic shock wave/turbulent boundary layer interaction to the three turbulence models.

Copyright

© 2017, the Authors. Published by Atlantis Press.

Open Access

This is an open access article distributed under the CC BY-NC license (http://creativecommons.org/licenses/by-nc/4.0/).

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TY  - CONF
AU  - Bei Yang
AU  - Ge Li
AU  - Chenyu Zhang
PY  - 2017/03
DA  - 2017/03
TI  - Numerical simulation on supersonic shock wave/turbulent boundary interaction
BT  - Proceedings of the 2016 International Forum on Mechanical, Control and Automation (IFMCA 2016)
PB  - Atlantis Press
SP  - 870
EP  - 874
SN  - 2352-5401
UR  - https://doi.org/10.2991/ifmca-16.2017.136
DO  - 10.2991/ifmca-16.2017.136
ID  - Yang2017/03
ER  -