I have recently been working quite a bit with SW flow sim and have gotten good results in 2D. I am working my way up and have now begun trying to tackle a 3D wing. Find my 2D simulation here: Lift Coefficient on 2D Airfoil
I have been able to somewhat successfully reach convergence for the 3D case. My concern is that even on a relatively powerful computer, calculation time is in the neighborhood of 24-30 hours. How can I keep this as low as possible yet ensure I am getting accurate results?
I am able to check values for this simulation, but the next step is to include the fuselage of my plane, and I will have nothing to compare with so I want to perfect my methods before moving on.
The wing I am simulating is built from the same airfoil as the 2D simulation.
Rather that go into details on the setup again, I will jump straight to my results and different methods I took.
The Mesh was created using a level 1 initial mesh with a level 5 refine set to refine every 1 travel starting with the 2nd full travel. The resulting mesh is pictured below.
The simulation converged after after 21 hours with a mesh of 5.75 million fluid cells + 320,000 partial cells. The converged value for CL is 0.317, off from the theoretical value by about 6%.
I am okay with the accuracy, but would like to know if there is a way that I could set the problem up differently to shorten the calculation time without bringing down the accuracy of the simulation.