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Fluent analysis for an airfoil

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Old   October 3, 2014, 05:51
Default Fluent analysis for an airfoil
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I am trying to solve for the flow characteristics and the forces on an airfoil in Fluent. It is a 2D analysis.

The mesh is a structured mesh. I used a symmetric airfoil to find out which solution method would give me the best results because i know that for a symmetric airfoil the lift is zero at an angle of attack equal to zero ( ideally ).

But for some reason (this is where i need help), none of the methods ( solution methods) gave me a lift close to zero.

For the airfoil i used, the Chord length was 5.16m and the maximum thickness of airfoil was 0.78m. The velocity of wind was taken to be 100 m/s.

For most of the methods( most of them were momentum defined by First order upwind ) yielded a Drag force which was approximately equal to 2352 N and a lift force that was equal to 23659 N. In the reference values in the solution setup, these were the values i entered :
Area : 0.78 m^2
Depth : 5.16 m
Length : 1 m.

Are the values that I have entered for Reference values correct ?

Can anyone please tell me what my mistake is?

Thanks a lot!
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Old   October 7, 2014, 10:43
David Stanbridge
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You need to provide the boundary conditions for the model. Posting a picture of the mesh would also help in understanding your set up.
David Stanbridge

Swift TG Solutions Limited
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Old   October 7, 2014, 13:15
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Kushal Puri
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what about the total temperature, pressure and static temperture and pressure.
Its a compressible flow simulation or incompressible
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airfoil, airfoil analysis

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