I’m trying to run a CFD simulation of my airfoil at varying angles of attack at 45 meters per second. My numbers are stabilizing after a few iterations for the Lift and Drag Coefficients and the Force Plots but the numbers just seem off to me.
The Drag Coefficient is going down as my Angle of Attack is going up which makes no sense to me. My Lift numbers also seem off.
The Force Plots are also showing a number I would expect to see for Pressure Force in the Z (Downforce) but the Pressure Force in the Y (Drag) seems really low.
Downforce and Drag are in lbf for the entire airfoil in this picture.
Hi Ryan, this is Fillia
The first thing I noticed about the project is the mesh and the sizing of the domain, so to begin with, I suggest you use the sizing (check Figure 6) according to this tutorial: Compressible Flow Around a Wing | Tutorial | SimScale
Keep in mind that you need to adjust the dimensions to the characteristics of your own model.
Also, I see that you used the same settings, but these have to be adjusted as well. As you might have noticed, the region refinements have a big maximum length size limitation, so they have no impact on the generated mesh:
