Numerical simulation on supersonic shock wave/turbulent boundary interaction
Bei Yang, Ge Li, Chenyu Zhang
Available Online March 2017.
- https://doi.org/10.2991/ifmca-16.2017.136How to use a DOI?
- turbulence model; numerical simulation; supersonic; shock wave; turbulence; heat transfer
- 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.
- Open Access
- This is an open access article distributed under the CC BY-NC license.
Cite this article
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 - https://doi.org/10.2991/ifmca-16.2017.136 ID - Yang2017/03 ER -