RCAIDE.Library.Components.Nacelles.Nacelle

Nacelle#

class Nacelle(*args, **kwarg)[source]#

Bases: Component

Base class for aircraft engine nacelles providing core functionality for geometric definition and analysis.

tag#

Unique identifier for the nacelle component, defaults to ‘nacelle’

Type:

str

origin#

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

Type:

list

aerodynamic_center#

3D coordinates [x, y, z] of the nacelle’s aerodynamic center, defaults to [0.0, 0.0, 0.0]

Type:

list

areas#

Collection of nacelle area measurements

  • front_projectedfloat

    Frontal area, defaults to 0.0

  • side_projectedfloat

    Side profile area, defaults to 0.0

  • wettedfloat

    Total wetted surface area, defaults to 0.0

Type:

Data

diameter#

Maximum diameter of the nacelle, defaults to 0.0

Type:

float

inlet_diameter#

Diameter of the engine inlet, defaults to 0.0

Type:

float

length#

Total length of the nacelle, defaults to 0.0

Type:

float

orientation_euler_angles#

Rotation angles [roll, pitch, yaw] in radians, defaults to [0.0, 0.0, 0.0]

Type:

list

flow_through#

Flag indicating if nacelle has flow passing through it, defaults to True

Type:

bool

has_pylon#

Flag indicating if nacelle is mounted on a pylon, defaults to True

Type:

bool

differential_pressure#

Pressure differential between internal and external flow, defaults to 0.0

Type:

float

cowling_airfoil_angle#

Angle of the cowling lip airfoil section, defaults to 0.0

Type:

float

Notes

The nacelle class provides the foundation for engine installation design, including:

  • Geometric definition capabilities

  • Coordinate transformation utilities

  • Integration with propulsion system analysis

Major Assumptions

  • Rigid body for structural analysis

  • Quasi-steady aerodynamics

Definitions

‘Nacelle Frame’

Local coordinate system with X out the nose, Z towards the ground, and Y out the right side

‘Vehicle Frame’

Aircraft coordinate system with X towards the tail, Z towards the ceiling, and Y out the right wing

See also

RCAIDE.Library.Components.Nacelles.Body_of_Revolution_Nacelle

Implementation for axisymmetric nacelles

RCAIDE.Library.Components.Nacelles.Stack_Nacelle

Implementation for stacked segment nacelles

append_operating_conditions(segment, energy_conditions, noise_conditions=None)[source]#

Placeholder for adding operating conditions to the nacelle.

Parameters:

  • segment (Data) – Flight segment data

  • propulsor (Data) – Propulsion system data

nac_vel_to_body()[source]#

Computes rotation matrix from nacelle velocity frame to body frame.

Returns:

3x3 rotation matrix

Return type:

ndarray

Notes

Assumes two nacelle frames: * Vehicle frame describing location * Velocity frame for aerodynamic calculations

body_to_nac_vel()[source]#

Computes rotation matrix from body frame to nacelle velocity frame.

Returns:

3x3 rotation matrix

Return type:

ndarray

Notes

Transformation sequence: 1. Body to vehicle frame 2. Vehicle to nacelle vehicle frame 3. Nacelle vehicle to nacelle velocity frame

vec_to_vel()[source]#

Computes rotation matrix from nacelle vehicle frame to nacelle velocity frame.

Returns:

3x3 rotation matrix

Return type:

ndarray