[Shaoming]

Hi all,

I am using Fluent to analyse a typical 3D wing problem under low Re. However, the CL which was obtained is way too high in region of 3.7 for AoA of 4!

(selected results from force report)
Force vector: (0.06976 0.997564 0)
pressure total pressure total
force force coefficient coefficient
n n
-------------- --------------
2.2806709 2.2830547 3.7235443 3.7274363
-------------- -------------- -------------- --------------
2.2806709 2.2830547 3.7235443 3.7274363

Could anyone help verify if the parameters used are suitable and correct?

Fluent
(grid checks and scaling have been carried out correctly)
Solver: Pressure-based
Materials: constant density and viscosity
Viscous Model: Spalart-Allmaras (at default values)
Operating Conditions: Op pressure = 101325 Pa
Boundary Conditions: (kindly refer to attached file)
Inlet-velocity inlet
Outlet-pressure outlet

Kindly point out any possible loopholes which i might have in the meshing as well. (FYI airfoil used is GEMINI, c=0.171m, b=1.2)

Thanks in advance!

[veera]

that first force vector is x component ?
x=sin alpha?

[veera]

dear seniors
actually i am simulating naca4412 3d airfoil wing for downloaded conference paper , in that paper i got results , but my solution is very low in the two order deviated from his values
for example . paper result is at 0 AOA , cl=0.0018, cd =-0.05
but my result is cl=0.0016, cd =0.00016
similarly at 5 AOA , PAPER RESULT IS CL=0.2 , CD = 0.1
but my result again cl= 0.0023 , cd = 0.0003
what any thing wrong in inlet parameters what i gave , or in scaling factor , waiting for your response