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Fluids

Naca0012 wing flow analysis

    • Arunkumarmoovandan37
      Subscriber
      Hi all I've simulated a naca0012 wing with chord of 0.1m, span of 0.3m velocity of 15m/s.nI've used k-epsilon turbulence model with velocity inlet and pressure outlet.nI'm interested in calculating aerodynamic forces.nI've used tetrahedral mesh with an element size of approximately 6million elements.n1st cell height is about 4e-5m.nWith k-epsilon model I could get a converged results. But the issue is convergence can be obtained from 0 degrees till 15 degree but after that convergence doesn't occur. I've tried increasing the number of iterations but nothing happens.nReference area for my wing is 0.03m2.nI've tried other turbulence models also but this time at any angle of attack I couldn't get a converged results.nPlease help to resolve this issue.n
    • DrAmine
      Ansys Employee
      Add some information about Yplus, Mesh Quality, Boundary Conditions, Solution Methods, Models Used and Domain picture. n
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