When I input the wing geometry with the angle of attack as part of the geometry, my results are close to those from other techniques (VLM, 3D panel methods), as well as reference texts. However, if I mesh the wing with a 0 deg AoA and try to impose the AoA at the inlet boundary by changing the flow vector, my results are not close.
I believe I may have a meshing issue, or a lack of understanding of the inlet flow boundary conditions.
Thanks! I have tried various mesh sizes, but I will go even larger on the next mesh. For some reason I haven’t been able to get boundary layer refinement to work when I use the parametric option–I almost immediately get an error message, even before a log is posted. I will review the CFD master class to see what I have missed…
Many thanks!
Thanks, Anna, this helped a great deal. Pawel also sent me a great tip, and I realized I had not visualized the flow field correctly. I changed my BCs to inlet-outlet as per the homework assignment and I am now getting reasonable answers.