use_api_core

cfg = {
    # Options
    'Threads': int, # number of threads (optional, default=1)
    'Verb': int, # verbosity (optional, default=1)
    # Model (geometry or mesh)
    'File': str, # Input file containing the model
    'Pars': dict, # parameters for input file model
    'Dim': int, # problem dimension (2 or 3)
    'Format': str, # save format (vtk or gmsh)
    # Markers...
    'Fluid': str, # name of physical group containing the fluid
    'Farfield': list of str, # LIST of names of physical groups containing the farfield boundaries (downstream should be last element)
    # ... only 2D
    'Wing': str, # name of physical group containing the airfoil boundary (will be the body of interest for aerostructural and optimization)
    'Wake': str, # name of physical group containing the wake
    'Te': str, # name of physical group containing the trailing edge
    # ... only 3D
    'Wings': list of str, # LIST of names of physical groups containing the lifting surface boundary (first element will be the body of interest for aerostructural and optimization)
    'Wakes': list of str, # LIST of names of physical group containing the wake
    'WakeTips': list of str, # LIST of names of physical group containing the free edge of the wake (not for 2.5D)
    'Tes': list of str, # LIST of names of physical group containing the trailing edges
    # ... optional for 3D
    'Symmetry': str, # name of physical group containing the symmetry boundaries
    'Fuselage': str, # name of physical group containing the fuselage boundary
    'WakeExs': str, # LIST of names of physical group containing the free edge of the wake and the intersection of lifting surface with fuselage (to be excluded from Wake B.C.), only required if a 'Fuselage' if present, otherwise 'WakeTips' is sufficient
    # Freestream
    'M_inf': float, # freestream Mach number (optional, default=0)
    'AoA': float, # freestream angle of attack [deg] (optional, default=0)
    'AoS': float, # freestream angle of sideslip [deg] (optional, default=0)
    'Q_inf': float, # freesteam dynamic pressure (only required for aerostructural computations)
    # Geometry
    'S_ref': float, # reference surface length
    'c_ref': float, # reference chord length
    'x_ref': float, # x-coordinate of reference point for moment computation
    'y_ref': float, # y-coordinate of reference point for moment computation
    'z_ref': float, # z-coordinate of reference point for moment computation
    # Numerical
    'LSolver': 'GMRES', # inner solver (PARDISO, MUMPS, SparseLU or GMRES)
    'G_fill': int, # fill-in factor for GMRES preconditioner (optional, default=2)
    'G_tol': float, # tolerance for GMRES (optional, default=1e-5)
    'G_restart': int, # restart for GMRES (optional, default=50)
    'Rel_tol': float, # relative tolerance on solver residual
    'Abs_tol': float, # absolute tolerance on solver residual
    'Max_it': int # maximum number of iterations for nonlinear solver
    }

from dart.api.core import init_dart
_dart = init_dart(cfg, scenario='aerodynamic', task='analysis', `viscous=False`)