buffalo_wings.airfoil.Naca4ModifiedAirfoilParamsSpec

class buffalo_wings.airfoil.Naca4ModifiedAirfoilParamsSpec(m=0.0, p=0.0, 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 4-digit airfoil.

Attributes

`m`	Maximum camber as a fraction of chord.
`p`	Chordwise location of maximum camber as a fraction of chord.
`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.

m: FloatScalar: Maximum camber as a fraction of chord.

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

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.