High Fidelity Simulation of the Turbulent Flow in a Transonic Axial Compressor

The present work proposes to use LES in a 3D transonic axial compressor configuration, the NASA Rotor 37. Three meshes are investigated: a 10 million, a 25 million and a 100 million grid points mesh. The convergence criteria, the choice of the numerical schemes and the determina- tion of the time-step are investigated to propose a methodology for LES calculations. The time needed to compute such simulations and comparison with the experimental results are given. Finally, an analysis of the mesh dependency for LES is assessed.

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