buffalo_wings.airfoil.AirfoilFactory

class buffalo_wings.airfoil.AirfoilFactory[source]

Bases: object

Construct public airfoil runtime objects from user-facing specs.

This factory centralizes the mapping from serialized airfoil schema objects to the concrete runtime classes used by the geometry library.

__init__()

Methods

`__init__`()
`from_spec`(spec)	Build an airfoil object from a schema definition.
`naca4_from_designation`(designation)	Build a classic NACA 4-digit airfoil from a designation.
`naca4_from_params`(*, m, p, t[, ...])	Build a parametric NACA 4-digit airfoil from explicit params.
`naca4_modified_from_designation`(designation)	Build a classic modified NACA 4-digit airfoil from a designation.
`naca4_modified_from_params`(*, m, p, t, ...)	Build a parametric modified NACA 4-digit airfoil from params.
`naca5_from_designation`(designation)	Build a classic NACA 5-digit airfoil from a designation.
`naca5_from_params`(*, ideal_lift_coefficient, ...)	Build a parametric NACA 5-digit airfoil from explicit params.
`naca5_modified_from_designation`(designation)	Build a classic modified NACA 5-digit airfoil from a designation.
`naca5_modified_from_params`(*, ...[, ...])	Build a parametric modified NACA 5-digit airfoil from params.

static from_spec(spec)[source]

Build an airfoil object from a schema definition.

Parameters:

spec (AirfoilDefinitionSpec) – Serialized airfoil definition to convert into a runtime object.

Returns:

Runtime airfoil instance corresponding to spec.

Return type:

Airfoil

Raises:

ValueError – If a NACA specification does not provide exactly one of designation or params.
NotImplementedError – If the airfoil type is not yet supported by the factory.

static naca4_from_designation(designation)[source]

Build a classic NACA 4-digit airfoil from a designation.

Parameters:: designation (str) – Four-digit NACA designation such as "2412".
Returns:: Runtime airfoil built from the classic designation.
Return type:: Naca4AirfoilClassic
Raises:: ValueError – If designation is not a valid 4-digit NACA code.

static naca4_from_params(*, m, p, t, trailing_edge='standard', leading_edge_radius='standard')[source]

Build a parametric NACA 4-digit airfoil from explicit params.

Parameters:

m (float) – Maximum camber as a fraction of chord.
p (float) – Chordwise location of maximum camber as a fraction of chord.
t (float) – Maximum thickness as a fraction of chord.
trailing_edge ({"standard", "sharp"}, default "standard") – Trailing-edge closure model for the thickness distribution.
leading_edge_radius ({"standard", "exact"}, default "standard") – Leading-edge radius treatment for the thickness distribution.

Returns:

Runtime airfoil built from the explicit parameters.

Return type:

Naca4AirfoilParams

Raises:

ValueError – If any parameter lies outside the supported NACA 4-digit range.

static naca4_modified_from_designation(designation)[source]

Build a classic modified NACA 4-digit airfoil from a designation.

Parameters:: designation (str) – Modified NACA 4-digit designation such as "0003-64".
Returns:: Runtime airfoil built from the modified-series designation.
Return type:: Naca4ModifiedAirfoilClassic
Raises:: ValueError – If designation is not a valid modified NACA 4-digit code.

static naca4_modified_from_params(*, m, p, t, leading_edge_index, max_thickness_location, trailing_edge='standard')[source]

Build a parametric modified NACA 4-digit airfoil from params.

Parameters:

m (float) – Maximum camber as a fraction of chord.
p (float) – Chordwise location of maximum camber as a fraction of chord.
t (float) – Maximum thickness as a fraction of chord.
leading_edge_index (float) – Modified-series leading-edge shape index.
max_thickness_location (float) – Chordwise location of maximum thickness as a fraction of chord.
trailing_edge ({"standard", "sharp"}, default "standard") – Trailing-edge closure model for the thickness distribution.

Returns:

Runtime airfoil built from the explicit parameters.

Return type:

Naca4ModifiedAirfoilParams

Raises:

ValueError – If any parameter lies outside the supported modified-series range.

static naca5_from_designation(designation)[source]

Build a classic NACA 5-digit airfoil from a designation.

Parameters:: designation (str) – Five-digit NACA designation such as "23012".
Returns:: Runtime airfoil built from the classic designation.
Return type:: Naca5AirfoilClassic
Raises:: ValueError – If designation is not a valid 5-digit NACA code.

static naca5_from_params(*, ideal_lift_coefficient, max_camber_location, reflexed, t, trailing_edge='standard', leading_edge_radius='standard')[source]

Build a parametric NACA 5-digit airfoil from explicit params.

Parameters:

ideal_lift_coefficient (float) – Design lift coefficient associated with the camber line.
max_camber_location (float) – Chordwise location of maximum camber as a fraction of chord.
reflexed (bool) – Whether to build the reflexed camber-line family.
t (float) – Maximum thickness as a fraction of chord.
trailing_edge ({"standard", "sharp"}, default "standard") – Trailing-edge closure model for the thickness distribution.
leading_edge_radius ({"standard", "exact"}, default "standard") – Leading-edge radius treatment for the thickness distribution.

Returns:

Runtime airfoil built from the explicit parameters.

Return type:

Naca5AirfoilParams

Raises:

ValueError – If any parameter lies outside the supported NACA 5-digit range.

static naca5_modified_from_designation(designation)[source]

Build a classic modified NACA 5-digit airfoil from a designation.

Parameters:: designation (str) – Modified NACA 5-digit designation string.
Returns:: Runtime airfoil built from the modified-series designation.
Return type:: Naca5ModifiedAirfoilClassic
Raises:: ValueError – If designation is not a valid modified NACA 5-digit code.

static naca5_modified_from_params(*, ideal_lift_coefficient, max_camber_location, reflexed, t, leading_edge_index, max_thickness_location, trailing_edge='standard')[source]

Build a parametric modified NACA 5-digit airfoil from params.

Parameters:

ideal_lift_coefficient (float) – Design lift coefficient associated with the camber line.
max_camber_location (float) – Chordwise location of maximum camber as a fraction of chord.
reflexed (bool) – Whether to build the reflexed camber-line family.
t (float) – Maximum thickness as a fraction of chord.
leading_edge_index (float) – Modified-series leading-edge shape index.
max_thickness_location (float) – Chordwise location of maximum thickness as a fraction of chord.
trailing_edge ({"standard", "sharp"}, default "standard") – Trailing-edge closure model for the thickness distribution.

Returns:

Runtime airfoil built from the explicit parameters.

Return type:

Naca5ModifiedAirfoilParams

Raises:

ValueError – If any parameter lies outside the supported modified-series range.