The following list outlines the xFoil inputs along with their default values available through the AIM interface.

• Mach = 0.0
  Mach number.
• Re = 0.0
  Reynolds number.
• Alpha = NULL
  Angle of attack [degree], either a single value or an array of values ( [0.0, 4.0, ...] ) may be provided.
• Alpha_Increment = NULL
  Angle of attack [degree] sequence - [first value, last value, increment].
• CL = NULL
  Prescribed coefficient of lift, either a single value or an array of values ( [0.1, 0.5, ...] ) may be provided.
• CL_Increment = NULL
  Prescribed coefficient of lift sequence - [first value, last value, increment].
• CL_Inviscid = NULL
  Prescribed inviscid coefficient of lift, either a single value or an array of values ( [0.1, 0.5, ...] ) may be provided.
• Append_PolarFile = False
  Append the file (xfoilPolar.dat) that polar data is written to.
• Viscous_Iteration = 100
  Viscous solution iteration limit. Only set if a Re isn't 0.0 .
• Num_Panel = 200
  Number of discrete panels.
• LETE_Panel_Density_Ratio = 0.25
  Panel density ratio between LE/TE.
• Write_Cp = False
  Have xFoil write the coefficient of pressure (Cp) distribution to a file - xfoilCp.dat.