buffalo_wings.airfoil.Naca5AirfoilParamsSpec

class buffalo_wings.airfoil.Naca5AirfoilParamsSpec(ideal_lift_coefficient=0.3, max_camber_location=0.15, reflexed=False, max_thickness=0.0, trailing_edge='standard', leading_edge_radius='standard')[source]

Bases: object

Explicit parameter definition for a NACA 5-digit airfoil.

Attributes

`ideal_lift_coefficient`	Ideal lift coefficient associated with the mean line.
`max_camber_location`	Chordwise location of maximum camber as a fraction of chord.
`reflexed`	Whether to use the reflexed 5-digit mean line.
`max_thickness`	Maximum thickness as a fraction of chord.
`trailing_edge`	Trailing-edge closure convention for the thickness law.
`leading_edge_radius`	Leading-edge radius convention for the thickness law.

ideal_lift_coefficient: FloatScalar: Ideal lift coefficient associated with the mean line.

max_camber_location: FloatScalar: Chordwise location of maximum camber as a fraction of chord.

reflexed: bool: Whether to use the reflexed 5-digit mean line.

max_thickness: FloatScalar: Maximum thickness as a fraction of chord.

trailing_edge: Literal['standard', 'sharp']: Trailing-edge closure convention for the thickness law.

leading_edge_radius: Literal['standard', 'exact']: Leading-edge radius convention for the thickness law.