Options

maxIters: int = 100

The maximum iterations for XFOIL solver. By default 100.

printRealConvergence: bool = True

Whether or not to print out the convergence history in real mode.

printComplexConvergence: bool = False

Whether or not to print out the convergence history in complex mode.

writeCoordinates: bool = True

If True, it will write airfoil coordinates to dat file when writeSolution is called. By default True.

writeSliceFile: bool = True

If True, it will save chordwise data in a pickle file when writeSolution is called. By default True.

writeSolution: bool = False

If True, it will call writeSolution when the solver is called with an AeroProblem. By default False).

plotAirfoil: bool = False

If True, it will show airfoil plot with cp and cf data when writeSolution is called. By default False.

outputDirectory: str = .

The directory to save the output files. By default the current directory.

numberSolutions: bool = True

If True, will add call counter to output file names. By default True.

xTrip: ndarray = numpy.full

The boundary layer trip location specified as a two-element numpy array where the first element is the chordwise location at which to trip the upper surface and the second is the chordwise location at which to trip the lower surface. By default will not trip the boundary layer and instead use XFOIL’s transition model.

nCrit: float = 9.0

The critical amplification exponent for boundary layer transition. This parameter represents the background turbulence level. Lower values will result in earlier turbulent transition.