buffalo_wings.airfoil.Naca45DigitThicknessParams

class buffalo_wings.airfoil.Naca45DigitThicknessParams(mti, closed_te, use_radius)[source]

Bases: Naca45DigitThicknessClassic

Parametric NACA 4-digit and 5-digit airfoil thickness.

The thickness is parameterized on the square root of the chord location where the thickness is desired. This is to remove singularities that occur at the leading edge for the typical chord length parameterization.

This class extends the standard thickness distribution relation by solving for coefficients from the original constraints even for non-integer parameters, allowing a closed trailing edge, and allowing the leading-edge radius condition to be enforced directly.

Notes

Specifying the same parameters as the classic thickness profile will not result in an identical thickness profile because the canonical coefficients do not match the stated constraints in the original source from Jacobs, Ward, and Pinkerton (1933).

Parameters:

mti (float)
closed_te (bool)
use_radius (bool)

__init__(mti, closed_te, use_radius)[source]

Initialize the parametric NACA thickness distribution.

Parameters:

mti (float) – Maximum-thickness index as a percent of chord.
closed_te (bool) – Whether the trailing edge closes to zero thickness.
use_radius (bool) – Whether to enforce the classic leading-edge radius condition.

Return type:

None

Methods

`__init__`(mti, closed_te, use_radius)	Initialize the parametric NACA thickness distribution.
`delta`(t)	Return the thickness at specified parameter location.
`delta_t`(t)	Return first derivative of thickness at specified parameter location.
`delta_tt`(t)	Return second derivative of thickness at specified parameter location.
`discontinuities`()	Return the locations of any discontinuities in the thickness.
`max_thickness_parameter`()	Return parameter coordinate of maximum thickness.

Attributes

`a`	Return the polynomial coefficients.
`closed_trailing_edge`	Return the trailing-edge closure flag.
`max_thickness_index`	Return the maximum-thickness index.
`use_leading_edge_radius`	Return the leading-edge treatment flag.

property a: ndarray[tuple[int, ...], dtype[float64]]

Return the polynomial coefficients.

Returns:: Coefficients for the classic thickness relation.
Return type:: buffalo_wings.type_aliases.FloatArray

property closed_trailing_edge: bool

Return the trailing-edge closure flag.

Returns:: True when the trailing edge closes to zero thickness.
Return type:: bool

delta(t)

Return the thickness at specified parameter location.

Parameters:: t (numpy.ndarray) – Parameter location of interest. Equal to the square root of the desired chord location.
Returns:: Thickness at specified parameter.
Return type:: numpy.ndarray

delta_t(t)

Return first derivative of thickness at specified parameter location.

Parameters:: t (numpy.ndarray) – Parameter location of interest. Equal to the square root of the desired chord location.
Returns:: First derivative of thickness at specified parameter.
Return type:: numpy.ndarray

delta_tt(t)

Return second derivative of thickness at specified parameter location.

Parameters:: t (numpy.ndarray) – Parameter location of interest. Equal to the square root of the desired chord location.
Returns:: Second derivative of thickness at specified parameter.
Return type:: numpy.ndarray

discontinuities()

Return the locations of any discontinuities in the thickness.

Returns:: Parametric coordinates of any discontinuities.
Return type:: List[float]

property max_thickness_index: float

Return the maximum-thickness index.

Returns:: Maximum thickness as a percent-chord index.
Return type:: float

max_thickness_parameter()

Return parameter coordinate of maximum thickness.

Returns:: Parameter coordinate of maximum thickness.
Return type:: float

property use_leading_edge_radius: bool

Return the leading-edge treatment flag.

Returns:: True when the classic leading-edge radius is enforced.
Return type:: bool