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, either a single value or an array of values ( [0.0, 4.0, ...] ) may be provided [degree].
- 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 = 20
Viscous solution iteration limit. Only set if a Re isn't 0.0 .
- Write_Cp = False
Have xFoil write the coefficient of pressure (Cp) distribution to a file - xfoilCp.dat.