RCAIDE.Library.Components.Wings.Wing

Wing

class Wing(*args, **kwarg)

Bases: Component

Base class for aircraft lifting surfaces providing core functionality for geometric definition and analysis.

tag

Unique identifier for the wing, defaults to ‘wing’

Type:

str

mass_properties

Mass and inertia properties, initialized empty

Type:

Mass_Properties

origin

3D coordinates [x, y, z] defining wing’s reference point, defaults to [0.0, 0.0, 0.0]

Type:

ndarray

symmetric

Flag indicating if wing is symmetric about x-z plane, defaults to True

Type:

bool

vertical

Flag indicating if wing is vertically oriented, defaults to False

Type:

bool

t_tail

Flag indicating if wing is mounted on vertical tail, defaults to False

Type:

bool

taper

Wing taper ratio, defaults to 0.0

Type:

float

dihedral

Wing dihedral angle, defaults to 0.0

Type:

float

aspect_ratio

Wing aspect ratio, defaults to 0.0

Type:

float

thickness_to_chord

Average thickness-to-chord ratio, defaults to 0.0

Type:

float

aerodynamic_center

Location of aerodynamic center [x, y, z], defaults to [0.0, 0.0, 0.0]

Type:

list

exposed_root_chord_offset

Offset of exposed root from centerline, defaults to 0.0

Type:

float

total_length

Total length of wing, defaults to 0.0

Type:

float

spans

Collection of span measurements

• projectedfloat

  Projected span, defaults to 0.0

• totalfloat

  Total span including dihedral effects, defaults to 0.0

Type:

Data

areas

Collection of area measurements

• referencefloat

  Reference area, defaults to 0.0

• exposedfloat

  Exposed area, defaults to 0.0

• affectedfloat

  Area affected by high-lift devices, defaults to 0.0

• wettedfloat

  Wetted area, defaults to 0.0

Type:

Data

chords

Collection of chord measurements

• mean_aerodynamicfloat

  Mean aerodynamic chord, defaults to 0.0

• mean_geometricfloat

  Mean geometric chord, defaults to 0.0

• rootfloat

  Root chord, defaults to 0.0

• tipfloat

  Tip chord, defaults to 0.0

Type:

Data

sweeps

Collection of sweep angles

• quarter_chordfloat

  Quarter-chord sweep angle, defaults to 0.0

• leading_edgefloat

  Leading edge sweep angle, defaults to None

• half_chordfloat

  Half-chord sweep angle, defaults to 0.0

Type:

Data

twists

Collection of twist angles

• rootfloat

  Root section twist angle, defaults to 0.0

• tipfloat

  Tip section twist angle, defaults to 0.0

Type:

Data

high_lift

Flag indicating presence of high-lift devices, defaults to False

Type:

bool

symbolic

Flag for symbolic computation mode, defaults to False

Type:

bool

high_mach

Flag for high Mach number flow, defaults to False

Type:

bool

vortex_lift

Flag for vortex lift modeling, defaults to False

Type:

bool

transition_x_upper

Upper surface transition location, defaults to 0.0

Type:

float

transition_x_lower

Lower surface transition location, defaults to 0.0

Type:

float

dynamic_pressure_ratio

Local to freestream dynamic pressure ratio, defaults to 0.0

Type:

float

Airfoil

Collection of airfoil definitions, initialized empty

Type:

Container

segments

Collection of wing segments, initialized empty

Type:

Container

control_surfaces

Collection of control surfaces, initialized empty

Type:

Container

fuel_tanks

Collection of fuel tanks, initialized empty

Type:

Container

Notes

The Wing class serves as the foundation for all lifting surfaces in RCAIDE. It provides:

• Geometric definition capabilities

• Segment management

• Control surface integration

• Fuel tank integration

• Mass properties computation

See also

RCAIDE.Library.Components.Wings.Main_Wing

Primary lifting surface implementation

RCAIDE.Library.Components.Wings.Horizontal_Tail

Horizontal stabilizer implementation

RCAIDE.Library.Components.Wings.Vertical_Tail

Vertical stabilizer implementation

append_segment(segment)

Adds a new segment to the wing’s segment container.

Parameters:

segment (Data) – Wing segment to be added

append_airfoil(airfoil)

Adds an airfoil definition to the wing.

Parameters:

airfoil (Data) – Airfoil data to be added

append_control_surface(control_surface)

Adds a control surface to the wing.

Parameters:

control_surface (Data) – Control surface to be added

append_fuel_tank(fuel_tank)

Adds a fuel tank to the wing.

Parameters:

fuel_tank (Data) – Fuel tank to be added

compute_moment_of_inertia(mass, center_of_gravity=[[0, 0, 0]], fuel_flag=False)

Computes the moment of inertia tensor for the wing.

Parameters:

• mass (float) – Wing mass

• center_of_gravity (list, optional) – Reference point coordinates, defaults to [[0, 0, 0]]

• fuel_flag (bool, optional) – Flag to include fuel mass, defaults to False

Returns:

3x3 moment of inertia tensor

Return type:

ndarray

class Container(*args, **kwarg)

Bases: Container

get_children()

Returns the components that can go inside

Assumptions: None

Source: N/A

Inputs: None

Outputs: None

Properties Used: N/A

class Container(*args, **kwarg)

Bases: Container

get_children()

Returns the components that can go inside

Assumptions: None

Source: N/A

Inputs: None

Outputs: None

Properties Used: N/A