# Fluent analysis for an airfoil

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 October 3, 2014, 05:51 Fluent analysis for an airfoil #1 New Member   Pratik Join Date: Jul 2014 Posts: 3 Rep Power: 12 Hello, 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!

 October 7, 2014, 10:43 #2 Member   David Stanbridge Join Date: Apr 2010 Location: Norwich, UK Posts: 59 Rep Power: 16 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 www.swifttgsolutions.com

 October 7, 2014, 13:15 #3 Senior Member   Kushal Puri Join Date: Nov 2013 Posts: 182 Rep Power: 12 what about the total temperature, pressure and static temperture and pressure. Its a compressible flow simulation or incompressible

 Tags airfoil, airfoil analysis