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Old   November 21, 2002, 06:20
Default low spped wing computation
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echo
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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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Old   November 21, 2002, 08:35
Default Re: low spped wing computation
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Rahul Hiwale
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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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Old   November 22, 2002, 08:33
Default Re: low spped wing computation
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echo
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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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Old   November 22, 2002, 12:31
Default Re: low spped wing computation
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An Modh Coinniolach
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Have you changed the options to select faces rather than edges in te Boundary Layer panel?
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Old   November 24, 2002, 01:47
Default Re: low spped wing computation
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mahdi saniee nezhad
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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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