def __defaults__(self):
self.tag = 'wing'
self.mass_properties = Mass_Properties()
self.position = [0.0, 0.0, 0.0]
self.symmetric = True
self.vertical = False
self.t_tail = False
self.sweep = 0.0
self.taper = 0.0
self.dihedral = 0.0
self.aspect_ratio = 0.0
self.thickness_to_chord = 0.0
self.span_efficiency = 0.9
self.aerodynamic_center = [0.0, 0.0, 0.0]
self.exposed_root_chord_offset = 0.0
self.spans = Data()
self.spans.projected = 0.0
self.areas = Data()
self.areas.reference = 0.0
self.areas.exposed = 0.0
self.areas.affected = 0.0
self.areas.wetted = 0.0
self.chords = Data()
self.chords.mean_aerodynamic = 0.0
self.chords.mean_geometric = 0.0
self.chords.root = 0.0
self.chords.tip = 0.0
self.twists = Data()
self.twists.root = 0.0
self.twists.tip = 0.0
self.control_surfaces = Data()
self.flaps = Data()
self.flaps.chord = 0.0
self.flaps.angle = 0.0
self.flaps.span_start = 0.0
self.flaps.span_end = 0.0
self.flaps.type = None
self.flaps.area = 0.0
self.slats = Data()
self.slats.chord = 0.0
self.slats.angle = 0.0
self.slats.span_start = 0.0
self.slats.span_end = 0.0
self.slats.type = None
self.high_lift = False
self.high_mach = False
self.vortex_lift = False
self.transition_x_upper = 0.0
self.transition_x_lower = 0.0
def __defaults__(self):
"""This sets the default values of a wing defined in SUAVE.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.tag = 'wing'
self.mass_properties = Mass_Properties()
self.origin = [[0.0, 0.0, 0.0]]
self.symmetric = True
self.vertical = False
self.t_tail = False
self.taper = 0.0
self.dihedral = 0.0
self.aspect_ratio = 0.0
self.thickness_to_chord = 0.0
self.span_efficiency = 0.9
self.aerodynamic_center = [0.0, 0.0, 0.0]
self.exposed_root_chord_offset = 0.0
self.spans = Data()
self.spans.projected = 0.0
self.areas = Data()
self.areas.reference = 0.0
self.areas.exposed = 0.0
self.areas.affected = 0.0
self.areas.wetted = 0.0
self.chords = Data()
self.chords.mean_aerodynamic = 0.0
self.chords.mean_geometric = 0.0
self.chords.root = 0.0
self.chords.tip = 0.0
self.sweeps = Data()
self.sweeps.quarter_chord = 0.0
self.sweeps.leading_edge = 0.0
self.sweeps.half_chord = 0.0
self.twists = Data()
self.twists.root = 0.0
self.twists.tip = 0.0
self.high_lift = False
self.high_mach = False
self.vortex_lift = False
self.transition_x_upper = 0.0
self.transition_x_lower = 0.0
self.Airfoil = Data()
self.Segments = SUAVE.Core.ContainerOrdered()
self.control_surfaces = SUAVE.Core.ContainerOrdered()
self.Fuel_Tanks = SUAVE.Core.Container()
def __defaults__(self):
"""This sets the default values of a wing defined in SUAVE.
Assumptions:
None
Source:
N/A
Inputs:
None
Outputs:
None
Properties Used:
N/A
"""
self.tag = 'wing'
self.mass_properties = Mass_Properties()
self.origin = [[0.0, 0.0, 0.0]]
self.symmetric = True
self.vertical = False
self.t_tail = False
self.taper = 0.0
self.dihedral = 0.0
self.aspect_ratio = 0.0
self.thickness_to_chord = 0.0
self.aerodynamic_center = [0.0, 0.0, 0.0]
self.exposed_root_chord_offset = 0.0
self.total_length = 0.0
self.spans = Data()
self.spans.projected = 0.0
self.spans.total = 0.0
self.areas = Data()
self.areas.reference = 0.0
self.areas.exposed = 0.0
self.areas.affected = 0.0
self.areas.wetted = 0.0
self.chords = Data()
self.chords.mean_aerodynamic = 0.0
self.chords.mean_geometric = 0.0
self.chords.root = 0.0
self.chords.tip = 0.0
self.sweeps = Data()
self.sweeps.quarter_chord = 0.0
self.sweeps.leading_edge = None
self.sweeps.half_chord = 0.0
self.twists = Data()
self.twists.root = 0.0
self.twists.tip = 0.0
self.high_lift = False
self.high_mach = False
self.vortex_lift = False
self.transition_x_upper = 0.0
self.transition_x_lower = 0.0
self.dynamic_pressure_ratio = 0.0
self.Airfoil = Data()
self.non_dimensional_origin = [[0.0, 0.0, 0.0]]
self.generative_design_minimum = 1
self.generative_design_max_per_vehicle = 5
self.generative_design_characteristics = [
'taper', 'aspect_ratio', 'thickness_to_chord', 'areas.reference',
'sweeps.quarter_chord', 'dihedral', 'non_dimensional_origin[0][0]',
'non_dimensional_origin[0][1]', 'non_dimensional_origin[0][2]'
]
self.generative_design_char_min_bounds = [
0, 1., 0.001, 0.1, 0.001, -np.pi / 4, -1., -1., -1.
]
self.generative_design_char_max_bounds = [
5., np.inf, 1.0, np.inf, np.pi / 3, np.pi / 4, 1., 1., 1.
]
self.Segments = ContainerOrdered()
self.control_surfaces = SUAVE.Core.Container()
self.Fuel_Tanks = SUAVE.Core.Container()