Negative CL at low negative AoA

[Sean van Hees]

Dear Rob,

For this design, I am obtaining negative values for the (induced) lift coefficient. I suspect this is caused by the tail located in the wake of the wing. I have tested this by altering the tail's dihedral angle (to (-)45 deg), which yielded positive CL at negative AoA. However, this does not resemble the system that I am analysing as this vehicle has the same dihedral angles for the wing and tail. What is the best way to approach this?

Thanks in advance,

Sean