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()