Learning Forum

[sahajthapa]

Hello everyone,

I am performing a 2-D simulating flow over NACA 0035 with AoA ranging from 0 to 15 degrees with k-wSST turbulence model and Re=0.139e6. The main problem occurs during computation of lift coefficient. For increasing AoA, the lift coefficient merely increases with the max lift of 0.03, however I am getting correct values for drag coefficient. I am comparing the results with XFOIL. At 6 degrees AOA, XFOIL gives CL of 0.33 however i am getting -0..03. Flow separation occur at 10 degrees AoA.

I rechecked the reference values and the vectors for velocity (cos(), sin()) and lift coefficient (-sin() , cos () ) but cannot find any problem at all.

For your reference,

Turbulence Model: k-w SST

Pressure-Velocity Coupling: SIMPLE

Reference Values:

Area+ 0.1016 m

Depth= 1 m (2-D)

Length = 0.1016 m (chord length)

y+ is ensured below 0.8. Number of elements: 23200, C-shaped domain for inlet.

Thank you for your time!!

[Rob]

How well resolved is the streamwise mesh and mesh in the wake region?

[sahajthapa]

Mesh is well resolved with minimum orthogonality of 0.9 and quality close to 1. I have attached the image for the mesh.
Thanks!