I am trying to perform a CFD simulation of a 70 degree sweep Delta Wing at different angles of attack (aoa = 20, 25, 30, 35 degrees). The inlet flow is at 25m/s. I have made a spherical Far-field boundary with the sphere radius of 5 times the root chord length of the delta wing. Because of the symmetrical shape only half of the delta wing and spherical far-field boundary is considered for meshing. I have made 10 inflation layers on the delta wing surface to capture the boundary layer and an unstructured mesh in the far-field using ICEM-CFD. A mesh with 0.7 million cells has been created. Since the Mach no. is low, I have run a steady state Pressure based simulation using SA turbulence model in Fluent. Density of air is taken as constant. The hemi-spherical boundary is taken as velocity inlet and the symmetry is applied at the symmetrical face. My y+ lies in the range of 0.1 - 0.6.(adsbygoogle = window.adsbygoogle || []).push({});

I want to know, have i made any mistake in the case setup?

what turbulence conditions i need to mention at the inlet velocity boundary condition?

I also want to perform simulations with k-w SST and k-epsilon turbulence models. Is my y+ enough for the simulations with the above mentioned turbulence models? Among all which is a relatively better turbulence model for subsonic CFD simulations of delta wings at high angles of attack?

Do i need to make a structured mesh?

Your guidance will be appreciated.

Best regards

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# Aerospace Delta wing cfd

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