Feasibility of Hybrid RANS-LES Modeling of Shock/Boundary-Layer Interaction in a Duct
A shock induced boundary-layer separation (SBLI) occurring in a duct at M = 1.4 has been analyzed using hybrid RANS-LES methods. The shock wave interacts with the turbulent wall boundary layers and triggers flow separation in the duct corners. The main purpose of the present work is to highlight the difficulties in modeling SBLI, particularly, when hybrid RANS-LES models are used. Results computed using different turbulence models are presented and discussed in comparison with available experimental data. Based on a number of simulations, some issues are addressed and some critical remarks are provided for potential improvements using turbulence-resolving modeling approaches in future work.
KeywordsShock Wave Coarse Grid Separation Bubble Shock Location Recirculation Bubble
Unable to display preview. Download preview PDF.
- 2.Bruce, P.J.K., Babinsky, H., Tartinville, B., Hirch, C.: An experimental and numerical study of an oscillating transonic shock wave in a duct. In: 48th AIAA Aerospace Science Meeting, Orlando, pp. 2010–2925 (2010)Google Scholar
- 4.Eliasson, P.: EDGE, a Navier-Stokes Solver for Unstructured Grids. Scientific report, FOI-R-0298-SE, Computational Aerodynamics Department, Aeronautics Division, FOI (2001)Google Scholar
- 6.Peng, S.-H.: Hybrid RANS-LES Modeling Based on Zero- and One-Equation Models For Turbulent Flow Simulation. In: Proceedings of the 4th International Symposium on Turbulence and Shear Flow Phenomena, Williamsburg (2005)Google Scholar
- 8.Spalart, P.R., Allmaras, S.R.: A One-Equation Turbulence Model for Aerodynamic Flows. La Recherche Aerospatiale 1, 5–21 (1994)Google Scholar
- 10.Spalart, P.R., Jou, W.-H., Strelets, M., Allmaras, R.: Comments on the Feasability of LES for Wings, and on a Hybrid RANS/LES Approach. In: Advances in DNS/LES, Ruston, Lousiana, pp. 137–147 (1997)Google Scholar