buffalo_wings.airfoil.Naca5ModifiedAirfoilParamsSpec

class buffalo_wings.airfoil.Naca5ModifiedAirfoilParamsSpec(ideal_lift_coefficient=0.3, max_camber_location=0.15, reflexed=False, max_thickness=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.

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.
`leading_edge_index`	Leading-edge index in the modified NACA thickness family.
`max_thickness_location`	Chordwise location of maximum thickness as a fraction of chord.
`trailing_edge`	Trailing-edge closure 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.

leading_edge_index: FloatScalar: Leading-edge index in the modified NACA thickness family.

max_thickness_location: FloatScalar: Chordwise location of maximum thickness as a fraction of chord.

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