# NACA 0012 2D validation

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 August 27, 2014, 06:50 NACA 0012 2D validation #1 New Member   Join Date: Aug 2014 Posts: 15 Rep Power: 4 I have no good experience to aerodynamic analysis. I did some assignments in University days but I want to laern more and doing the validation as per given from here http://turbmodels.larc.nasa.gov/naca0012_val.html. However I first run at angle of 10 deg but I get very small Cl. I think I am doing some mistake in setup or calculation. Few questions... I read in books that in 2D, the lift coefficient Cl is per unit span length, so the equation for coefficient of lift is: cl_2D=Lift per span length/(0.5 * rho * V^2 * C) In 3D it is CL_3D=Lift/(0.5 * rho * V^2 * A) C is chord length, and rho and V are the freestream conditions and A is planform area.. Now, if I do 2D simulation in fluent, How do I calculate cl_2D coefficient in 2D manually using above formula? Is this Cl calculation would tally with the NASA validation data? Sorry for my poor English, its not my first language

 September 1, 2014, 06:16 #2 Senior Member   OJ Join Date: Apr 2012 Location: United Kindom Posts: 475 Rep Power: 12 Lift/span in 3D should be equal to Lift produced in 2D simulation in FLUENT and the Cl data should match with results

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