buffalo_wings.airfoil.Naca5AirfoilParamsSpec

class buffalo_wings.airfoil.Naca5AirfoilParamsSpec(ideal_lift_coefficient=0.3, max_camber_location=0.15, reflexed=False, t=0.0, trailing_edge='standard', leading_edge_radius='standard')[source]

Bases: object

Explicit parameter definition for a NACA 5-digit airfoil.

Parameters:

ideal_lift_coefficient (float)
max_camber_location (float)
reflexed (bool)
t (float)
trailing_edge (Literal['standard', 'sharp'])
leading_edge_radius (Literal['standard', 'exact'])

ideal_lift_coefficient

Design lift coefficient associated with the mean camber line.

Type:: float, default 0.3

max_camber_location

Chordwise location of maximum camber as a fraction of chord.

Type:: float, default 0.15

reflexed

Whether the camber line uses the reflexed 5-digit family.

Type:: bool, default False

t

Maximum thickness as a fraction of chord.

Type:: float, default 0.0

trailing_edge

Trailing-edge closure model used for the thickness distribution.

Type:: {"standard", "sharp"}, default "standard"

leading_edge_radius

Leading-edge radius treatment used for the thickness distribution.

Type:: {"standard", "exact"}, default "standard"

__init__(ideal_lift_coefficient=0.3, max_camber_location=0.15, reflexed=False, t=0.0, trailing_edge='standard', leading_edge_radius='standard')

Parameters:

ideal_lift_coefficient (float)
max_camber_location (float)
reflexed (bool)
t (float)
trailing_edge (Literal['standard', 'sharp'])
leading_edge_radius (Literal['standard', 'exact'])

Return type:

None

Methods

__init__([ideal_lift_coefficient, ...])

Attributes

`ideal_lift_coefficient`
`max_camber_location`
`reflexed`
`t`
`trailing_edge`
`leading_edge_radius`