August 9, 2020 at 5:58 amzein.elserfySubscriber
I am simulatin flow over aerofoil NACA 0018 using Compressible SST model. The computational domain is extended 3c (chord length) upstream, 3c to top and bottom boundaries and 6 c downstream. The fluid is air and density is calculated according to ideal gas law and viscoity is calculated according to sutherland.The boundary conditions used is velocity inlet (ux,0,0) for the left boundary and pressure outlet for top,bottom and right boundary and the front and back boundaries are set to periodic. when i ran the simulation, the residual did not converageNovember 13, 2020 at 2:19 pmKRAdministratorHello It looks like your question was answered here. Please refrain from creating duplicate posts for the same question to ensure streamlined user experience. I'm closing this post.
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