Abstract
The transitional flow over Aerospatiale A-airfoil at critical angle of attack is simulated using DDES and IDDES models. This airfoil features relatively thick boundary layer and a mild separation around trailing edge. Simulation results based on three different grid system and reference data from LESFOIL project are compared. Time averaged velocity profiles, Reynolds stress and vortical structures are presented. The results of DDES model show the consistency on different grid system but fail to predict the fluctuation of flow field. IDDES model is able to resolve the fluctuation but overpredict the resolved quantities than experimental data. Also different grid system with different length scale for LES model have much effect on IDDES results.
Published Version
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