[Freestream]

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!

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Capture 2.PNG

[Freestream]

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

[Freestream]

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.