Hi, this is my first attempt to use CFD to characterize a lifting surface aerodynamic coefficient.
I’ve setup a simple simulation where I evaluated a wing at cruise speed & 0deg AOA Force et Moment and it’s aerodynamic coefficients.
However, I’m a bit confused, I’m getting a lift coefficient of 0.3834.
Using the ref Surface of 0.408 m^2, ref free stream velocity of 13.9 m/s and air density of 1.1965 kg/m^3, get a lift force of 18.08 N. However, looking at the force résultat, the Z force is computed at 15.11
Additionally, the lift coefficient much different of the one provided by openvsp which use a vortex lattice method. The VLM evaluates the lift at 0.2422
I am misunderstanding something?
ps. I’m also concerned of my trailing edge meshing, what could I do to fix it?