The following list outlines the xFoil outputs available through the AIM interface.
- Alpha = Angle of attack value(s).
- CL = Coefficient of lift value(s).
- CD = Coefficient of drag value(s).
- CD_p = Coefficient of drag value(s), pressure contribution.
- CM = Moment coefficient value(s).
- Cp_Min = Minimum coefficient of pressure value(s).
- Transition_Top = Value(s) of x- transition location on the top of the airfoil.
- Transition_Bottom = Value(s) of x- transition location on the bottom of the airfoil.