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.
• LE_Rbar = Leading edge radius of the airfoil, normalized by chord.
• Chord = Input airfoil chord length.