RCAIDE.Library.Components.Wings.Blended_Wing_Body

Blended_Wing_Body

class Blended_Wing_Body(*args, **kwarg)

Bases: Main_Wing

A blended wing body (BWB) design that smoothly integrates the wing and fuselage into a single lifting body configuration.

tag

Unique identifier for the BWB fuselage component, defaults to ‘bwb_fuselage’

Type:

str

aft_center_body.area

Cross-sectional area of the aft centerbody section in square meters

Type:

float

aft_center_body.taper

Taper ratio of the aft centerbody section, defined as the ratio of tip to root chord lengths

Type:

float

cabin_area

Total available cabin floor area in square meters

Type:

float

Notes

The blended wing body design offers several advantages over conventional tube-and-wing configurations:

• Reduced wetted area leading to lower skin friction drag

• Improved lift-to-drag ratio due to the lifting body design

• Potential for increased internal volume and better weight distribution

Definitions

‘Centerbody’

The central section of the BWB that houses the passenger cabin and cargo hold

‘Aft Centerbody’

The rear section of the centerbody that transitions into the outer wing sections

See also

RCAIDE.Library.Components.Fuselages.Fuselage

Base fuselage class that provides common functionality

compute_moments_of_inertia(vehicle, center_of_gravity=[[0, 0, 0]])

Computes the moment of inertia tensor for the wing.

Parameters:

• 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

compute_center_of_gravity(vehicle)

Computes the center of gravity for the wing.

See also

RCAIDE.Library.Methods.weights.vehicle.center_of_gravity.compute_fuselage_center_of_gravity

Implementation of the center of gravity calculation

append_cabin(cabin)

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

Parameters:

segment (Data) – Fuselage segment to be added