buffalo_wings.airfoil.Naca5ModifiedAirfoilParamsSpec

class buffalo_wings.airfoil.Naca5ModifiedAirfoilParamsSpec(ideal_lift_coefficient=0.3, max_camber_location=0.15, reflexed=False, 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 5-digit airfoil.

Parameters:

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

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

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__(ideal_lift_coefficient=0.3, max_camber_location=0.15, reflexed=False, t=0.0, leading_edge_index=1.0, max_thickness_location=0.1, trailing_edge='standard')

Parameters:

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

Return type:

None

Methods

__init__([ideal_lift_coefficient, ...])

Attributes

`ideal_lift_coefficient`
`max_camber_location`
`reflexed`
`t`
`leading_edge_index`
`max_thickness_location`
`trailing_edge`