buffalo_wings.airfoil.Naca4ModifiedAirfoilParamsSpec

class buffalo_wings.airfoil.Naca4ModifiedAirfoilParamsSpec(m=0.0, p=0.0, t=0.0, leading_edge_index=1.0, max_thickness_location=0.1, trailing_edge='standard')[source]

Bases: object

Explicit parameter definition for a modified NACA 4-digit airfoil.

Parameters:

m (float)
p (float)
t (float)
leading_edge_index (float)
max_thickness_location (float)
trailing_edge (Literal['standard', 'sharp'])

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

leading_edge_index

Modified-series leading-edge shape index.

Type:: float, default 1.0

max_thickness_location

Chordwise location of maximum thickness as a fraction of chord.

Type:: float, default 0.1

trailing_edge

Trailing-edge closure model used for the thickness distribution.

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

__init__(m=0.0, p=0.0, t=0.0, leading_edge_index=1.0, max_thickness_location=0.1, trailing_edge='standard')

Parameters:

m (float)
p (float)
t (float)
leading_edge_index (float)
max_thickness_location (float)
trailing_edge (Literal['standard', 'sharp'])

Return type:

None

Methods

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

Attributes

`m`
`p`
`t`
`leading_edge_index`
`max_thickness_location`
`trailing_edge`