buffalo_wings.airfoil.Naca4AirfoilParamsSpec

class buffalo_wings.airfoil.Naca4AirfoilParamsSpec(m=0.0, p=0.0, t=0.0, trailing_edge='standard', leading_edge_radius='standard')[source]

Bases: object

Explicit parameter definition for a NACA 4-digit airfoil.

Parameters:

m (float)
p (float)
t (float)
trailing_edge (Literal['standard', 'sharp'])
leading_edge_radius (Literal['standard', 'exact'])

m

Maximum camber as a fraction of chord.

Type:: float, default 0.0

p

Chordwise location of maximum camber as a fraction of chord.

Type:: float, default 0.0

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__(m=0.0, p=0.0, t=0.0, trailing_edge='standard', leading_edge_radius='standard')

Parameters:

m (float)
p (float)
t (float)
trailing_edge (Literal['standard', 'sharp'])
leading_edge_radius (Literal['standard', 'exact'])

Return type:

None

Methods

__init__([m, p, t, trailing_edge, ...])

Attributes

`m`
`p`
`t`
`trailing_edge`
`leading_edge_radius`