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November 21, 2002, 05:20
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low spped wing computation
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Guest
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I am using Fluent6.0 to computate lift/drag ratio of straight wing with aspect ration 12.The airfoil is NFL1050,the computational result of lift/drag ratio is too small,only about 20. The solver is segeregated solver,I have refined grid around the front edge. I have computated 2D airfoil,the result is fine. Who can tell me How I can get good result of wing?
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November 21, 2002, 07:35
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Re: low spped wing computation
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#2 |
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Guest
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Are you using boundary layer around wing geometry ? Also don't use constant viscosity. For high speed better to go for couple solver. Rahul
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November 22, 2002, 07:33
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Re: low spped wing computation
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#3 |
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Guest
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Thank you I have used boundary layer in 2D airfoil, but I can't generate Boundary layer around 3D wing. How I can do it?
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November 22, 2002, 11:31
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Re: low spped wing computation
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#4 |
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Have you changed the options to select faces rather than edges in te Boundary Layer panel?
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November 24, 2002, 00:47
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Re: low spped wing computation
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#5 |
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Guest
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Dear sir I have a problem with this title. If it's possible for you please send me your received responses. Very thanks for your attention to my request. With the best regards. Mahdi saniee nezhad
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