Problem with Angle of attack study. When using k-epsilon and 3. WING 150x40x40 mesh and 3. WINGLET 150x40x40 mesh.
Tried to methods for both wing and winglet.
3. WING CASE and 3.WINGLET CASE with only changing inlet velocity at boundary conditions.
Does not work for ANGLES OF ATTACK.
Second method for both.
AOA 3.WING CASE
Inlet outlet boundary conditions with pressure ->zero gradient, velocity for my angle of attack, and for k and e i did try both fixed value and inlet-outlet as well.
same for AOA .3 WINGLET CASE
I want to get result with 0 ,3, 6, 9degree AOA for my 3… MESH 150x40x40.
yesterday i did change my stl file to a step file and used inflate boundary layer but , i wanty to use above case - K-e as mention.
any advice ? need to write my report tomorrow