# NACA 0012, AOA=0, Lift=/0

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 September 25, 2016, 01:15 NACA 0012, AOA=0, Lift=/0 #1 New Member   jiyou Join Date: Sep 2016 Posts: 5 Rep Power: 9 Hi everyone, I am a final year student in University of Glasgow doing Aeronautical Engineering. I am doing a project of numerical study on NACA 0012 in ANSYS Fluent. I have read/watched tutorial on several sites and in Youtube over a month now. Right now i am using a C grid and structured mesh with the following parameters (Refer to image): AOA=0 Chord = 1m X Distance upstream of airfoil = 7m X Distance downstream of airfoil = 14m Edge Sizing Control: Number of Division = 100 Bias Factor = 150 Mapped Face Meshing No. of Elements = 40,269 Under Setup for simulation: Turbulence Model: K-e (Standard) Inlet Velocity = 5 m/s in x direction The rest are as default values. The result of force in the x and y direction are as follow (Retrieved from Result>Report>Forces>: Forces in the (x,y,z): 0.068348119, -0.0029689099, 0 (N) It is evident that the force in y direction is non zero (-0.0029689099). Hope to seek guidance from experienced user! Cheers! Capture 1.PNG Capture 2.PNG

 September 29, 2016, 23:02 #2 New Member   jiyou Join Date: Sep 2016 Posts: 5 Rep Power: 9 Hi everyone, i have an update on the result. i attempt to refined the mesh and employ SA turbulence model with coupled solution scheme. At Re=3e6 the lift coefficient results i have are as follow. AOA Cl Actual Cl** 0 -0.000715261 0.00 3 0.14828294 0.32 6 0.29564536 0.65 9 0.43876878 1.00 12 0.56909866 1.25 15 0.6879697 1.55 **Actual Cl data approximated from Abbot and Von Doenhoff's Theory of Wing Sections (page 462-463, reproduced below). The 2D lift coefficient is extracted from Report>Result>Force by the following expression: L=F_y cos alpha + F_x sin alpha Hope experienced Fluent user can help me with the discrepancies observed from the simulation. Thanks

 October 4, 2016, 03:36 #3 New Member   jiyou Join Date: Sep 2016 Posts: 5 Rep Power: 9 Hi everyone, i have resolved the problem by simply rotating the airfoil in Design Modeler, instead of resolving input velocity in the x and y direction. the result have shown that fault lies in this area, but i cannot explain for this phenomenon.

 Tags lift, mesh, naca 0012, turbulence model, validation